stc authorization letter els b737-400 msn 25110 and msn ...b737-400 4. type (aircraft, engine,...

GenAero

2 0 7 2 0 7 S a n t i l l a n e A v e , C o r a l G a b l e s , F L 3 3 1 3 4

T e l e p h o n e : ( 3 0 5 ) 4 4 5 - 2 1 2 4 * s a l e s @ g e n a e r o . n e t M A N U F A C T U R I N G

Engineering Data Packages * FAA DER Services * FAA STC’s * Installation Services Manufacturers of Audio and Video Entertainment Systems *

A V I O N I C S E N G I N E E R I N G

September 29, 2016 Mr. Jerome Basile VX Capital 915 Front St, San Francisco, CA 94403 Subject: Right to Use STC # SA3169SO - EASA.IM.A.S.02759 – EHS GA37-EHS-AFMS01 Dear Mr. Basile: This letter provides the required authorization to use GenAero STC # SA3169SO - EASA.IM.A.S.02759 for the installation of ATC Elementary Surveillance on VX Capital B737-400 aircraft. This Authorization is limited to aircraft serial numbers MSN 25110 and MSN 25111 only. The installer must determine compatibility of this data with the aircraft configuration. Any engineering changes must be provided to GenAero for review and approval. Is it also required that you incorporate this modification into the maintenance task cards to assure continued airworthiness of the modification. Please note that the Documentation is provided to you on an “as is” basis, without warranty of any kind, expressed or implied. In no event shall GenAero (General Aerospace) be liable for any damages resulting from the use of the STC or the Data Package. You acceptance of the documentation serves to hold General Aerospace harmless for any liability arising out of the use of such documentation. If you have any questions regarding the terms of this STC authorization use, please call me anytime. Sincerely,

Miguel Flores Manager

General Aerospace Inc. Flight Manual Supplement 207 Santillane Avenue Elementary Surveillance System (ELS), Coral Gables, FL 33134 and Enhanced Surveillance System (EHS) EASA STC No: EASA.IM.A.S.02759 _____________________________________________________________________________________________________

_____________________________________________________________________________________________________ EASA Approved Date: 30. July 2009 Dwg. No. GA37-ELS/EHS-AFMS01 Page 1 of 3 Rev. I/R

EUROPEAN AVIATION SAFETY AGENCY APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT

FOR AN

ELEMENTARY SURVEILLANCE (ELS) AND

ENHANCED SURVEILLANCE SYSTEM (EHS) INSTALLATION

IN A BOEING B737-200/300/400/500 SERIES AIRCRAFT

Registration No.:

Serial No.: This supplement must be attached to the basic EASA Approved Airplane Flight Manual when the airplane is modified by the installation of ELEMENTARY SURVEILLANCE (ELS) AND ENHANCED SURVEILLANCE SYSTEM (EHS) INSTALLATION in accordance with EASA Supplemental Type Certificate (STC) EASA.IM.A.S.02759 This document must be carried on the airplane at all times. The information contained herein, supplements or supersedes the basic Airplane Flight Manual only in those areas listed. For limitations, procedures and performance information not contained in this supplement, consult the basic Airplane Flight Manual.

EASA Approved: by STC EASA.IM.A.S.02759 EUROPEAN AVIATION SAFETY AGENCY Date: 30. July 2009

miguelflores

Typewritten Text

miguelflores

Typewritten Text

N778AS

miguelflores

Typewritten Text

miguelflores

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Typewritten Text

25110



LOG OF REVISIONS

Revision No. Description Pages Revised Approved By Date

I/R

Initial Release

All

EASA

30. July 2009



I. LIMITATIONS

• The installed Mode-S system satisfies the data requirements of ICAO DOC 7030/4, Regional Supplementary Procedures for SSR Mode-S Enhanced Surveillance in designated airspace. The system is capable of transmitting data parameters shown in the table I.1.

PARAMETER AVAILABLE/NOT AVAILABLE Aircraft Identification (Flight ID) Available

Capability Report Available Pressure Altitude Available

Magnetic Heading Available Indicated Airspeed Available

MACH No. Available Vertical Rate Available Roll Angle Available

Track Angle Rate Available True Track Angle Available

Ground Speed Available Selected Altitude Available

Barometric Pressure Setting Available

Table I.1

• In the event of conflict between ATC directives and TCAS equipment resolution advisory, comply with aircraft resolution advisory.

The limitations and information contained herein either supplement or, in the case of conflict, override those in the flight manual.

To be inserted in the flight manual and record sheet amended accordingly.



EUROPEAN AVIATION SAFETY AGENCY APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT

FOR AN

ELEMENTARY SURVEILLANCE (ELS) AND

ENHANCED SURVEILLANCE SYSTEM (EHS) INSTALLATION

IN A BOEING B737-200/300/400/500 SERIES AIRCRAFT

Registration No.:

Serial No.: This supplement must be attached to the basic EASA Approved Airplane Flight Manual when the airplane is modified by the installation of ELEMENTARY SURVEILLANCE (ELS) AND ENHANCED SURVEILLANCE SYSTEM (EHS) INSTALLATION in accordance with EASA Supplemental Type Certificate (STC) EASA.IM.A.S.02759 This document must be carried on the airplane at all times. The information contained herein, supplements or supersedes the basic Airplane Flight Manual only in those areas listed. For limitations, procedures and performance information not contained in this supplement, consult the basic Airplane Flight Manual.

EASA Approved: by STC EASA.IM.A.S.02759 EUROPEAN AVIATION SAFETY AGENCY Date: 30. July 2009

miguelflores

Typewritten Text

miguelflores

Typewritten Text

N779AS

miguelflores

Typewritten Text

miguelflores

Typewritten Text

miguelflores

Typewritten Text

25111

miguelflores

Typewritten Text



LOG OF REVISIONS

Revision No. Description Pages Revised Approved By Date

I/R

Initial Release

All

EASA

30. July 2009



I. LIMITATIONS

• The installed Mode-S system satisfies the data requirements of ICAO DOC 7030/4, Regional Supplementary Procedures for SSR Mode-S Enhanced Surveillance in designated airspace. The system is capable of transmitting data parameters shown in the table I.1.

PARAMETER AVAILABLE/NOT AVAILABLE Aircraft Identification (Flight ID) Available

Capability Report Available Pressure Altitude Available

Magnetic Heading Available Indicated Airspeed Available

MACH No. Available Vertical Rate Available Roll Angle Available

Track Angle Rate Available True Track Angle Available

Ground Speed Available Selected Altitude Available

Barometric Pressure Setting Available

Table I.1

• In the event of conflict between ATC directives and TCAS equipment resolution advisory, comply with aircraft resolution advisory.

The limitations and information contained herein either supplement or, in the case of conflict, override those in the flight manual.

To be inserted in the flight manual and record sheet amended accordingly.

U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION

STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS

1. DATE September 29, 2016

AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE BOEING

3. MODEL NO. B737-400

4. TYPE (Aircraft, Engine, Propeller, etc.) AIRPLANE

5. NAME OF APPLICANT VX Capital

LIST OF DATA 6. IDENTIFICATION 7. TITLE

GA-VX40-0916-EO REV. I/R DATED 09/28/16

ENGINEERING ORDER – B737-400 – ATC System upgrade for Elementary and Enhanced Surveillance. APROVAL HEREIN FOR THE ELECTRICAL DATA ONLY (NOT AN INSTALLATION APPROVAL) ON AIRCRAFT SERIAL NUMBER MSN 25110, N778AS ONLY. DATA BASED ON STC SA3169SO. ----------------END--------------------------END -------------------------------END-------------------------------

8. PURPOSE OF DATA To upgrade the ATC System with ELS and EHS provisons.

9. APPLICABLE REQUIREMENTS (List specific sections) 14 CFR 25.1301 (a) Amdt 25-0 14 CFR 25.1431 (c) Amdt 25-113

10. CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under 14 CFR Part 183, data listed above and on attached sheets numbered N/A have been examined in accordance with established procedures and found to comply with applicable requirements of the Airworthiness Standards listed.

Recommend approval of these data I (We) Therefore Approve these data

11.SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE(S)

12. DESIGNATION NUMBERS(S)

13. CLASSIFICATION(S)

DERT-510122-CE SYSTEMS AND EQUIPMENT

FAA Form 8110-3 (03-10) SUPERSEDES PREVIOUS EDITION

MIGUEL FLORES

U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION

STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS

1. DATE September 29, 2016

AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE BOEING

3. MODEL NO. B737-400

4. TYPE (Aircraft, Engine, Propeller, etc.) AIRPLANE

5. NAME OF APPLICANT VX Capital

LIST OF DATA 6. IDENTIFICATION 7. TITLE

GA-VX40-0916-EO REV. I/R DATED 09/28/16

ENGINEERING ORDER – B737-400 – ATC System upgrade for Elementary and Enhanced Surveillance. APROVAL HEREIN FOR THE ELECTRICAL DATA ONLY (NOT AN INSTALLATION APPROVAL) ON AIRCRAFT SERIAL NUMBER MSN 25111, N779AS ONLY. DATA BASED ON STC SA3169SO. ----------------END--------------------------END -------------------------------END-------------------------------

8. PURPOSE OF DATA To upgrade the ATC System with ELS and EHS provisons.

9. APPLICABLE REQUIREMENTS (List specific sections) 14 CFR 25.1301 (a) Amdt 25-0 14 CFR 25.1431 (c) Amdt 25-113

10. CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under 14 CFR Part 183, data listed above and on attached sheets numbered N/A have been examined in accordance with established procedures and found to comply with applicable requirements of the Airworthiness Standards listed.

Recommend approval of these data I (We) Therefore Approve these data

11.SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE(S)

12. DESIGNATION NUMBERS(S)

13. CLASSIFICATION(S)

DERT-510122-CE SYSTEMS AND EQUIPMENT

FAA Form 8110-3 (03-10) SUPERSEDES PREVIOUS EDITION

MIGUEL FLORES

REVISIONS REV DESCRIPTION DATE APPROVED I/R Initial Release 09/28/16 MFC

Notice: This is confidential and proprietary information of General Aerospace and may not be used or disclosed by the recipient without the prior written consent of General Aerospace and then only in accordance with specific written instructions of General Aerospace. By receipt hereof, in addition to any obligation the recipient has under any confidentiality agreement, contract, or license with General Aerospace, neither recipient nor its agents, representatives or employees will copy, reproduce or distribute this information, in whole or in part, at any time, without the prior written consent of General Aerospace and that it will keep confidential all information contained herein

GENERALAEROSPACE

932 Ponce de Leon Blvd. Coral Gables, FL 33134

ENGINEER M. Castel

CHECKED L.S.

APPROVED M. Flores

ENGINEERING ORDER B737-400 – ATC System upgrade for Elementary and

Enhanced Surveillance

SCALE: SIZE: CAGE CODE: DWG NO: REV: I/R NONE A 0LL76 GA-VX40/0916/EO Page 1 OF 19


Title: B737-400 – ATC System upgrade for Elementary and Enhanced Surveillance.

1.0 SUMMARY:

This Engineering Order will install all wiring required for the activation of Elementary (ELS) capabilities and Enhanced Surveillance (EHS). In addition existing ATC Transponders and ATC Control Panel will be replaced with new Elementary and Enhanced Surveillance compatible LRU’s.

2.0 AIRCRAFT:

MSN 25110 - 25111

3.0 AUTHORIZATION:

FAA STC # SA3169SO

EASA AFMS EASA.IM.A.S.02759. FAA DER FORM 8110-3.

4.0 CLASSIFICATION: Major Alteration

5.0 WEIGHT AND BALANCE CHANGE: Negligible.

6.0 ELECTRICAL LOAD CHANGE: 115 VAC Elex Power # 1 Item Removed Load Added Load Bus Affected Total Mode-S No.1 -------- 50 Watts 115 VAC Elex Power # 1 + 50 Watts Old ATC No.1 45 Watts -------- 115 VAC Elex Power # 1 -45 Watts

An increase of 5 Watts on the 115 VAC Elex Power # 1.

115 VAC Elex Power # 2 Item Removed Load Added Load Bus Affected Total Mode-S No.2 -------- 50 Watts 115 VAC Elex Power # 1 + 50 Watts Old ATC No.2 45 Watts -------- 115 VAC Elex Power # 1 -45 Watts

An increase of 5 Watts on the 115 VAC Elex Power # 2.


7.0 PUBLICATIONS AFFECTED:

7.1 Wiring Diagram Manual – Chapter 22, 34, 91. 7.2 Maintenance Manual – Chapter 34. 7.3 Illustrate Parts Catalog – Chapter 34.

8.0 REFERENCES:

8.1 Boeing Standard Wiring Practices Manual D6-54446. 8.2 General Aerospace FAA STC # SA3169SO. 8.3 General Aerospace EASA AFMS # EASA.IM.A.S.02759.

9.0 DRAWINGS:

Drawing Number Revision Nomenclature

GA-VX40/0916-1 I/R, 09/28/16 B737-400 ELS/EHS Component Location GA-VX40/0916-7 I/R, 09/28/16 B737-400 ATC No. 1 GA-VX40/0916-8 I/R, 09/28/16 B737-400 Elementary/Enhanced Surveillance

System No. 1 GA-VX40/0916-9 I/R, 09/28/16 B737-400 ATC No. 2 GA-VX40/0916-10 I/R, 09/28/16 B737-400 Elementary/Enhanced Surveillance

System No. 2 GA-VX40/0916-13 I/R, 09/28/16 ATC Transponder Tray Verification GA373-ATC-GT I/R, 05/17/05 Ground Test Plan- Dual Mode S Transponder

B737-200/300/-400/-500 Series


10.0 TOOLS:

10.1 ATC-601, Software level 3.04R or later, IFR System or equivalent.

11.0 SECTIONS:

11.1 Parts List. 11.2 Accomplishment Instructions. 11.3 Wiring and Installation Checkout.


Section: 11.1

GENERAL AEROSPACE ENGINEERING ORDER

MATERIAL LIST

Parts Required

Item Total Required Part Number Description

Vendor

1 2 822-1338-003 Mode-S Transponder Collins 2 1 G7490-30 or equiv. Flight ID/ATC/TCAS CTL

PNL Gables

3 A/R M27500-22G2T14 2/6/9/ or equivalent

Wire – DTS

4 A/R MS22759/16-22-9 or equivalent

Wire – Single 22

5 A/R MS22759/16-24-9 or equivalent

Wire – Single 24

6 A/R 324484 or equivalent Splice


Section 11.2

GENERAL AEROSPACE ENGINEERING ORDER

ACCOMPLISHMENT INSTRUCTIONS Description

This Engineering Order will install all wiring required for the Elementary Surveillance/Enhanced Surveillance (ELS/EHS) capabilities to the Mode-S transponders. In addition, existing ATC/TCAS Control Panel will be replaced with new Elementary Surveillance compatible Control Panel and the existing ATC Transponders will be replaced with ELS/EHS compatible units.

Reference: Installation drawings, Aircraft Maintenance Manual and Boeing Standard Wiring

Practices Manual.

NOTE: All work to be accomplished in accordance with Boeing Standard Wiring Practices Manual D6-54446. Remove all panels required to accomplish this modification.

A. Access Panels

A.1. Remove power from the airplane as specified in the B737 Maintenance Manual

Subject 24-22-00 or your equivalent procedure. _______________________ ______________________

Accomplished By Inspected By

A.2. On the P6 and P18 panels open the following circuit breakers and attach “DO NOT CLOSE” tags: • ATC-1 • ATC-2 • TCAS • ATC ANT RF SW

_______________________ ______________________



Section 11.2 Cont’

A.3. Get access to the items shown below:

1. In the flight deck: • Open P8 Panels

2. In the Electronic Equipment Compartment: • Gain access to E2-2 and E2-4 Electronic Shelf.

3. If required, remove access panels to route wires from E2-2 shelf and E2-4 Shelf.

4. Remove any additional panels required to perform this modification.

_______________________ ______________________


A.4. Remove ATC-1 and ATC-2 Transponders and send to stores for disposition. Record part number and serial number of removed LRU’s. ATC-1 ATC-2 P/N OFF: _______________ P/N OFF: ___________________

S/N OFF: _______________ S/N OFF: ___________________ _______________________ ______________________ Accomplished By Inspected By

A.5. Remove TCAS/Mode-S Control Panel and send to stores for disposition. Record part number and serial number of removed panel. P/N OFF: _______________

S/N OFF: _______________ _______________________ ______________________ Accomplished By Inspected By



B. E2 Shelf Removal

Caution: Ensure that power is removed from aircraft prior to performing this modification.

B.1. Gain Access to E/E Bay.

_______________________ ______________________ Accomplished By Inspected By

B.2. Remove all equipment installed on E1-2, E1-3, E2-2, and E2-4 Shelves and store for later re-installation.


B.3. Remove E1-2, E1-3, E2-2, and E2-4 shelves and retain attaching hardware. Note: Take care to ensure that all electrical disconnects are disengaged prior to

shelf removal. _______________________ ______________________ Accomplished By Inspected By



C. Mode-S No.1 & No.2 Shelf E2-2 and E2-4 Existing Wiring Modification

Mode-S # 1 – E2-2 Shelf

C.1. Locate wire W017-020-24 on Mode-S # 1 connector D149A. Remove wire from connector D149A, pin K5. Cap and stow wire near Mode-S connector using Boeing Standard Practices. Refer to drawing GA-VX40/0916-7. _______________________ ______________________

Accomplished By Inspected By C.2. Locate wire W017-037-24 on Mode-S # 1 connector D149B. Remove wire from

connector D149B, pin K3. Cap and stow wire near Mode-S connector using Boeing Standard Practices. Refer to drawing GA-VX40/0916-7.

_______________________ ______________________


C.3. Install SDI Wire W017-9545-24 (Jumper Wire) between pins G3 and J3 of D149A (TP). Refer to drawing GA-VX40/0916-7. _______________________ ______________________

Accomplished By Inspected By Mode-S # 2 – E2-4 Shelf C.4. Locate wire W087-002-24 on Mode-S # 2 connector D155A. Remove wire from

connector D155A, pin K5. Cap and stow wire near Mode-S connector using Boeing Standard Practices. Refer to drawing GA-VX40/0916-9.

_______________________ ______________________


C.5. Install SDI Wire W087-9546-24 (Jumper Wire) between pins G3 and J3 of D155A (TP). Refer to drawing GA-VX40/0916-9. _______________________ ______________________



D. Elementary/Enhanced Surveillance ATC-1 New E2-2 Shelf Wiring Installation

D.1. Obtain the required wire from stores and identify wire in accordance with drawing GA-VX40/0916-8 . Terminate wires per drawing GA-VX40/0916-8. Refer to drawing GA-VX40/0916-1 for ATC-1 location. Label splices in accordance with Boeing standard practices. _______________________ ______________________

Accomplished By Inspected By D.2. Secure new Elementary/Enhanced Surveillance No. 1 wire harness on E2-2 shelf

following existing wire bundles on the shelf according to Boeing Standard Wiring Practices Manual D6-54446.

_______________________ ______________________

Accomplished By Inspected By D.3. Terminate Elementary/Enhanced Surveillance-1 ground wires on E2-2 shelf in

accordance with Boeing Standard Wiring Practices Manual D6-54446. Refer to drawing GA-VX40/0916-8. Clean ground surface in accordance with Boeing Standard Wiring Practices Manual D6-54446, ref. 20-20-00.

_______________________ ______________________

Accomplished By Inspected By D.4. Terminate any remaining ATC-1 E2-2 shelf wiring according to drawings

GA-VX40/0916-7 and GA-VX40/0916-8.


D.5. Verify used grounds and splices are properly identified.




E. Elementary/Enhanced Surveillance ATC-2 New E2-4 Wiring Installation

E.1. Obtain the required wire from stores and identify wire in accordance with drawing GA-VX40/0916-10. Terminate wires per drawing GA-VX40/0916-10. Refer to drawing GA-VX40/0916-1 for ATC-2 location. Label splices in accordance with Boeing standard practices.

_______________________ ______________________

Accomplished By Inspected By E.2. Secure new Elementary/Enhanced Surveillance-2 wire harness on E2-4 shelf

following existing wire bundles on the shelf according to Boeing Standard Wiring Practices Manual D6-54446.

_______________________ ______________________


E.3. Terminate Elementary/Enhanced Surveillance-2 ground wires on E2-4 shelf in accordance with Boeing Standard Wiring Practices Manual D6-54446. Refer to drawing GA-VX40/0916-10. Clean ground surface in accordance with Boeing Standard Wiring Practices Manual D6-54446, ref. 20-20-00.

_______________________ ______________________


E.4. Terminate any remaining ATC-2 E2-4 shelf wiring according to drawings GA-VX40/0916-9 and GA-VX40/0916-10.

_______________________ ______________________


E.5. Verify used grounds and splices are properly identified.




F. ATC/TCAS/FLT ID Control Panel Wiring Modification

F.1. On Control Panel Connector D211, cap and stow wires W177-013-24 on pin 11 and wire W177-020-24 on pin 20. Refer to drawings GA-VX40/0916-7. _______________________ ______________________


F.2. On Control Panel Connector D519, cap and stow wire W247-012-24 on pin 11. Refer to Drawing GA-VX40/0916-9. _______________________ ______________________


G. Interface Wiring Modification

ATC-1 – IRU-1 Interface Wires G.1. Obtain applicable wires from stores for ATC No.1-IRU-1 interface. Modify IRU

wiring to TCAS on E2-2 in accordance with drawing GA-VX40/0916-8. Terminate wires per drawing GA-VX40/0916-8. All wires to be terminated and secured per Boeing Standard Wiring Practices Manual D6-54446.

_______________________ ______________________


ATC-1 – FMC Interface Wires G.2. Obtain applicable wires from stores for ATC No.1 – FMC interface. Route wires

W461-9016-22R/9017-22B from E2-2 shelf to E1-2 shelf following existing wire bundles. Terminate wires per drawing GA-VX40/0916-8. All wires to be routed and secured per Boeing Standard Wiring Practices Manual D6-54446.

_______________________ ______________________




G.3. Route wires W007-9001-24R/9002-24B on the rear of E1-2 shelf following existing

wire bundles. Terminate wires per drawing GA-VX40/0916-8. All wires to be routed, terminated and secured per Boeing Standard Wiring Practices Manual D6-54446.

_______________________ ______________________


ATC-1 – MCP Interface Wires G.4. Obtain applicable wires from stores for ATC No.1 – MCP interface. Route wires


_______________________ ______________________


G.5. Route wires W011-9000-24R/9001-24B on the rear of E1-3 shelf following existing wire bundles. Terminate wires per drawing GA-VX40/0916-8. All wires to be routed and secured per Boeing Standard Wiring Practices Manual D6-54446.

_______________________ ______________________




ATC-2 – IRU-2 Interface Wires

G.6. Obtain applicable wires from stores for ATC No.2-IRU-2 interface. Route wires W451-9020-22R/9021-22B from E2-4 shelf to E1-2 shelf following existing wire bundles. Terminate wires per drawing GA-VX40/0916-10. All wires to be routed and secured per Boeing Standard Wiring Practices Manual D6-54446.

_______________________ ______________________


G.7. Obtain applicable wires from stores and identify as W009-9003-22R/9004-22B. Route wires on the rear of E1-2 shelf following existing wire bundles. Terminate wires per drawing GA-VX40/0916-10. All wires to be routed and secured per Boeing Standard Wiring Practices Manual D6-54446.

_______________________ ______________________


ATC-2 – FMC Interface Wires G.8. Obtain applicable wires from stores for ATC No.2 – FMC interface. Route wires


_______________________ ______________________



Section 11.2 Cont’ G.9. Obtain applicable wires from stores and identify wires as W007-9005-24R/9006-

24B. Route wires on the rear of E1-2 shelf following existing wire bundles. Terminate wires per drawing GA-VX40/0916-10. All wires to be routed and secured per Boeing Standard Wiring Practices Manual D6-54446.

_______________________ ______________________


ATC-2 – MCP Interface Wires G.10. Obtain applicable wires from stores for ATC No.2 – MCP interface. Route wires


_______________________ ______________________

Accomplished By Inspected By G.11. Obtain applicable wires from stores. Identify wires as W069-9000-24R/9001-24B.

Route wires on the rear of E1-3 shelf following existing wire bundles. Terminate wires per drawing GA-VX40/0916-10. All wires to be routed and secured per Boeing Standard Wiring Practices Manual D6-54446.

_______________________ ______________________




G.12. Terminate Elementary/Enhanced Surveillance No. 1 Interface grounds and splices in accordance with Boeing Standard Wiring Practices Manual D654446. Refer to drawing GA-VX40/0916-8. Clean ground surface in accordance with Boeing Standard Wiring Practices Manual D6-54446, ref. 20-20-00.

_______________________ ______________________


G.13. Terminate Elementary/Enhanced Surveillance No. 2 Interface grounds and splices in accordance with Boeing Standard Wiring Practices Manual D654446. Refer to drawing GA-VX40/0916-10. Clean ground surface in accordance with Boeing Standard Wiring Practices Manual D6-54446, ref. 20-20-00.

_______________________ ______________________



Section 11.3

Description: This section will check all the wiring installed and verifies proper operation of aircraft navigation and communication equipment

A. Wiring Check out

CAUTION: Ensure that power is removed from aircraft prior to performing this operation.

A.1. Install previously removed shelves E1-2, E1-3, E2-2, and E2-4.


A.2. Perform a continuity check on all wiring installed during this installation in accordance with reference drawings.

_______________________ ______________________


A.3. Verify that all newly installed or disturbed connectors are properly identified. Use labels and decals provided on installation kit.

_______________________ ______________________


A.4. Install all equipment removed to perform this modification. Secure all shelves disconnects.

_______________________ ______________________


A.5. Verify TCAS, ATC-1, ATC-2, and ATC ANT RF SW circuit breakers are open.



SECTION 11.3 Con’t

A.6. Close areas opened during this installation. Refer to AMM for proper procedure.


A.7. Verify all areas opened during this installation for condition and security. Refer to

AMM for proper procedure.

_______________________ ______________________ Accomplished By Inspected By B. Mode-S Equipment installation

B.1. Verify correct connector keying before installing new Mode-S transponders. Refer to drawing GA-VX40/0916-13.

_______________________ ______________________


B.2. Install MODE-S Transponder No.1 and No.2 P/N: 822-1338-003 or equivalent and secure to tray. Record the serial numbers of the ATC transponders installed. Position: ___________ Position: _______________ P/N: _______________ P/N: ___________________

S/N: _______________ S/N: ___________________


B.3. Install new Control Panel P/N: G7490-39 or equiv. Record the part number and serial number of that panel. Refer to drawing GA-VX40/0916-1 for panel location. P/N: ___________________

S/N: ___________________


B.4. Power Aircraft (Refer to Maintenance Manual Procedure). Remove Collars from TCAS, ATC-1, ATC-2, and ATC ANT RF SW circuit breakers and push circuit breakers.

_______________________ ______________________



SECTION 11.3 Con’t C. Ground Test

C.1. Perform ATC system Ground Test Procedure in accordance with General Aerospace Ground Test Procedure, document number GA373-ATC-GT.

_______________________ ______________________


C.2. Return aircraft to its normal condition.

_______________________ ______________________ Accomplished By Inspected By ------------------------------------END OF EO------------------------------------------------------------

SCALE: SIZE: CAGE CODE: DWG NO: REV: I/R NONE A 0LL89 GA373-ATC-GT Page 1 of 31

GROUND TEST PLAN DUAL MODE S TRANSPONDER

Test Performed by: ____________________________________ Aircraft Registration: ____________________________________ Aircraft Serial No: ____________________________________ Date: ____________________________________

Notice: This is confidential and proprietary information of General Aerospace and may not be used or disclosed by the recipient without the prior written consent of General Aerospace and then only in accordance with specific written instructions of General Aerospace. By receipt hereof, in addition to any obligation the recipient has under any confidentiality agreement, contract, or license with General Aerospace, neither recipient nor its agents, representatives or employees will copy, reproduce or distribute this information, in whole or in part, at any time, without the prior written consent of General Aerospace and that it will keep confidential all information contained herein.

GENERAL AEROSPACE

932 Ponce de Leon Blvd. Coral Gables, FL 33134

ENGINEER O. Obando 05/17/05

CHECKED E. Brenes 05/17/05

APPROVED M. Flores 05/17/05

Ground Test Plan – Dual Mode S Transponder B737-200/-300/-400/-500 Series


Use and disclosure shall be in accordance with the proprietary legend located on the cover of this document

LOG OF REVISIONS

Revision No. Description Pages Revised Date Approved by

I/R Initial Release All 05/17/05 MFC



TABLE OF CONTENTS

1. PURPOSE...........................................................................................................................................................................4

2. GENERAL ..........................................................................................................................................................................4

3. REFERENCES...................................................................................................................................................................4

4. EQUIPMENT .....................................................................................................................................................................4

5. PREPARE ATC SYSTEM FOR TEST..............................................................................................................................5

6. ATC TRANSPONDER TESTS ..........................................................................................................................................5 A. EVALUATE SELF-TEST FEATURES AND FAILURE MODE ANNUNCIATORS....................................................................................5 B. PRESSURE ALTITUDE INTERFACE TEST .................................................................................................................................7 C. ATC MODE-S #1 PARAMETER TEST....................................................................................................................................13

a. Transponder Parameter Selection Test.............................................................................................................................................13 b. Mode-S Address Test.......................................................................................................................................................................13 c. Reply Delay .....................................................................................................................................................................................14 d. Reply Jitter.......................................................................................................................................................................................14 e. ATCRBS Reply Test .......................................................................................................................................................................14 f. SLS Level ........................................................................................................................................................................................15 g. Reply Frequency Test ......................................................................................................................................................................15 h. SPR ON/OFF Test ...........................................................................................................................................................................15 i. Diversity Test...................................................................................................................................................................................15 j. MTL Difference...............................................................................................................................................................................16 k. Transmit Power/Receiver Sensitivity...............................................................................................................................................16 l. Squitter Test.....................................................................................................................................................................................17 m. Mode S Formats Test. ......................................................................................................................................................................17 n. ELS/EHS Test..................................................................................................................................................................................18

1. Flight ID.....................................................................................................................................................................................18 2. Selected Vertical Intent Report Test ..........................................................................................................................................18 3. Data Link Capability Report ......................................................................................................................................................19 4. Track and Turn Report...............................................................................................................................................................20 5. Heading and Speed Report.........................................................................................................................................................20

D. ATC MODE-S #2 PARAMETER TEST .....................................................................................................................................22 a. Transponder Parameter Selection Test.............................................................................................................................................22 b. Mode-S Address Test.......................................................................................................................................................................22 c. Reply Delay .....................................................................................................................................................................................23 d. Reply Jitter.......................................................................................................................................................................................23 e. ATCRBS Reply Test .......................................................................................................................................................................24 f. SLS Level ........................................................................................................................................................................................24 g. Reply Frequency Test ......................................................................................................................................................................24 h. SPR ON/OFF Test ...........................................................................................................................................................................24 i. Diversity Test...................................................................................................................................................................................25 j. MTL Difference...............................................................................................................................................................................25 k. Transmit Power/Receiver Sensitivity...............................................................................................................................................25 l. Squitter Test.....................................................................................................................................................................................26 m. Mode S Formats Test. ......................................................................................................................................................................26 n. ELS/EHS Test..................................................................................................................................................................................27

1. Flight ID.....................................................................................................................................................................................27 2. Selected Vertical Intent Report Test ..........................................................................................................................................27 3. Data Link Capability Report ......................................................................................................................................................28 4. Track and Turn Report...............................................................................................................................................................29 5. Heading and Speed Report.........................................................................................................................................................29

E. ATC RETURN THE AIRCRAFT TO ITS NORMAL CONFIGURATION...............................................................................................30 7. TEST TRACKING FORM ...............................................................................................................................................31



1. PURPOSE

This document provides procedures that will meet or exceed the requirements as outlined in AC20-131A (Draft) for the ground test paragraphs for follow-on Supplemental Type Certification of Mode S Transponder Systems. These procedures are not required for subsequent installations using the STC but these tests, or a variation of them, are recommended for subsequent installations.

2. GENERAL

The procedures in this document assume that a complete installation checkout has been accomplished. It is also assumed that the person performing the tests has a working knowledge of the Mode-S ATC Transponder System installed in this aircraft. It is not necessary to follow the exact order of the test procedures as they are listed. It is up to the discretion of the person(s) performing the tests as to what order is the most logical to perform the tests. This test must be done following the specific directions in the Ramp Test Set Operation’s Manual to access the require parameters.

3. REFERENCES

Boeing 737 Maintenance Manual subjects: 24-22-00, 32-09-10, 34-12-00 and 34-53-00. Aeroflex “Operation Manual ATC – 601”. Flight ID/ATC/TCAS Control Panel, Gables, “Installation Manual”, 1st G7490-() Rev 02. Mode-S Data Link Transponder System, Honeywell, “System Description and Installation Manual”, No.

A09-3839-001, Revision 2. FAA AC20-131B, FAA, “Airworthiness Approval of Traffic Alert and Collision Avoidance Systems

(TCAS II) and Mode-S Transponders”. FAA Part 25, FAA, “Federal Aviation Regulations, Part 25- Airworthiness Standards – Transport

Category Airplanes”. ARINC 718-4, ARINC, “Air Traffic Control Transponder”. FAA PART 91.413.

4. EQUIPMENT

A. Required equipment.

1. Pitot-Static Test Set. 2. ATCRBS/Mode S Transponder Ramp Test Set IFR 601, Software Version 3.03 or later.



5. PREPARE ATC SYSTEM FOR TEST CAUTION: Do not place the Remote Test Set Antenna closer than 15 inches (0.40 meters) to the

aircraft antenna with the Test Set ON. This will cause damage to the Test Set.

1. Put the test set antenna at a convenient bearing and distance from the antennas under test. NOTE: The test set antenna must be within the line of sight of the ATC antennas.

2. Put the Test Set antenna in position towards the airplane antenna. 3. Connect the coax cable from the remote test set antenna to the test set. 4. Make sure the following circuit breakers are closed:

No.1 Air Data CMPTR 26 VAC No.1 Air Data CMPTR AC ALTM-1 ALTM-2 ATC-1 ATC Ant Switch ATC-2 No. 2 Air Data CMPTR26 VAC No. 2 Air Data CMPTR AC

6. ATC Transponder Tests

A. Evaluate self-test features and failure mode annunciators.

1. Make sure the panel did not energize with any failures. On the Flight ID/ATC/TCAS

Control Panel set the Transponder Select Switch to position “1” and make sure the “CP 1 FAIL” message is not shown. Then set the Transponder Select Switch to position “2” and make sure the “CP 2 FAIL” message is not shown. Set the Function Select Mode Switch to “XPNDR” position.

NOTE: If a failure is found, “CP 1 FAIL”, “CP 2 FAIL”, “0000” or “00000000” is shown on

the display.


2. Verify that the “XPNDR FAIL” lamp is extinguished on the Flight ID/ATC/TCAS Control

Panel.




A. Evaluate self-test features and failure mode annunciators Con’t. 3. On the Flight ID/ATC/TCAS Control Panel, press the TEST pushbutton for approximately

one second. Verify the following events:

Display window shows “88888888”. “XPNDR FAIL”, “ATC” and “FID” lights illuminate for approximately 3 seconds. Messages “CP2 PASS” and “CP1 PASS” are displayed. “XPNDR FAIL” extinguishes and “ATC” or “FID” light remains energized.


4. Pull the “No.2 Air Data CMPTR” circuit breaker. Verify the “XPNDR FAIL” lamp

illuminates on the Flight ID/ATC/TCAS Control Panel.


5. Reset the “No.2 Air Data CMPTR” circuit breaker. Verify that the lamp extinguishes.

_______________________ ______________________


6. Pull the “ATC-2” circuit breaker. Verify the “XPNDR FAIL” lamp illuminates on the Flight ID/ATC/TCAS Control Panel.

_______________________ ______________________


7. Reset the ATC-2 circuit breaker. Verify that the lamp extinguishes. _______________________ ______________________


8. On the Flight ID/ATC/TCAS Control Panel, set the Transponder Select Switch to position “1”. Pull the “No.1 Air Data CMPTR” circuit breakers. Verify that “XPNDR FAIL” lamp illuminates on the Flight ID/ATC/TCAS Control Panel.

_______________________ ______________________


9. Reset the “No.1 Air Data CMPTR” circuit breakers and verify that the lamp extinguishes. _______________________ ______________________




A. Evaluate self-test features and failure mode annunciators Con’t. 10. Pull the ATC-1 circuit breaker. Verify that “XPNDR FAIL” lamp illuminates on the Flight

ID/ATC/TCAS Control Panel.


11. Reset the ATC-1 circuit breakers and verify that the lamp extinguishes.

_______________________ ______________________


B. Pressure Altitude Interface Test

This test will verify that the pressure altitude source is properly interfaced to the Mode-S Transponders. The reported altitude should be within 125 feet of the expected altitude. Altitude reported may be compared to the respective altimeter readings.

WARNING: Prepare the safety – sensitive systems for the air mode before you open the AIR/GND

circuit breakers. In the Air Mode, many of the airplane systems can operate and cause injuries to persons and damage to equipment.

NOTE: The test set is a source of interference for radio and L-band radar equipment operating

near the test set. To avoid possible interference turn the test set off as soon as test is completed or when you must perform other radio checks on the airplane.

1. Override the Ground Safety Relay to simulate an airborne condition.


2. On the Flight ID/ATC/TCAS Control Panel set Transponder Select Switch to position “1”, press ATC/FID Select Mode Pushbutton Switch until the “ATC” annunciator is energized, and set the Function Select Mode Switch to “XPNDR” position.

3. Make sure air cannot go into the system when you supply the vacuum.

4. Remove all power from the autopilot (flight control) system. Refer to B737 AMM 22-11-

01/501.



B. Pressure Altitude Interface Test Cont’ 5. Open the following circuit breakers on the Circuit Breaker Panel, P18 and attach DO NOT-

CLOSE tags: Capt-Upper L Capt-Lower R F/O Upper R F/O Lower L Elevator Pitot L Elevator Pitot R Temp Probe Alpha Vane HTR R Alpha Vane HTR L

WARNING: MAKE SURE THAT YOU DO NOT APPLY ELECTRICAL POWER TO THE

FLIGHT CONTROLS. FLIGHT CONTROL SURFACES CAN MOVE AUTOMATICALLY WHEN YOU PRESSURIZE THE PITOT-STATIC SYSTEM. THIS CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.

6. Open the following circuit breaker on P6-2 panel and attach a DO-NOT-CLOSE tag:

FLAP LOAD RELIEF

CAUTION: MAKE SURE THAT YOU FLUSH THE PROBE ADAPTER WITH WATER BEFORE YOU ATTACH THE ADAPTER TO THE PROBE. YOU CAN CAUSE DAMAGE TO THE PROBE OR THE ADAPTER.

_______________________ ______________________


7. Flush the adapter for the Pitot-Static probe with water before you install it on the probe. Refer to AMM 34-11-01/501.

NOTE: Use a solution that has equal parts of ethylene glycol and water in temperatures between 32ºF and –40ºF.

_______________________ ______________________


8. Put vinyl adhesive tape on the drain hole for the Pitot chamber on the top left and right probes. Refer to AMM 34-11-01/501.

_______________________ ______________________




B. Pressure Altitude Interface Test Cont’ CAUTION: BE CAREFUL WITH THE TEST HOSES. INSTALL THE TEST ADAPTER AND TEST

HOSES SO THAT YOU DO NOT ADD WEIGHT TO THE PROBES. FAILURE TO DO THIS COULD CAUSE DAMAGE TO THE PROBE OR PUT THE PROBE OUT OF THE ALIGNED POSITION.

9. Connect the Pitot-Static Test Set to the No.1 Air Data System per Boeing 737 AMM Subject

34-11-01/501.

CAUTION: FLOW RESTRICTORS, CONTROL VALVES, AND CUTOFF VALVES MUST BE CONTAINED IN THE AIR DATA TEST SET.

_______________________ ______________________

Accomplished By Inspected By 10. Set the Captain’s and First Officer’s Altimeter to 29.92 inches of mercury. 11. Apply static pressure to achieve a pressure altitude of 1,500 feet. Apply Pitot pressure to achieve

airspeed of 150 knots.

12. Using the ATCRBS/Mode S Transponder Ramp Test Set, interrogate the selected transponder in the ATCRBS Reply Test mode. Verify the transmitted pressure altitude is 1,500 feet. Record altitude readings.

ATC-1 Observed Value: _______________ ATC-2 Observed Value: _______________

_______________________ ______________________


NOTE: ATC-2 values to be obtained after step 26.

13. Vary the static pressure on the Pitot-Static Test Set to achieve a pressure altitude of 3,000 feet.

14. Verify on the ATCRBS/Mode S Transponder Ramp Test Set that the transmitted pressure altitude is 3,000 feet. Record altitude readings.


_______________________ ______________________





B. Pressure Altitude Interface Test Cont’

16. Verify on the ATCRBS/Mode S Transponder Ramp Test Set that the transmitted pressure altitude is 6,000 ±125 feet. Record altitude readings.


_______________________ ______________________


17. Vary the static pressure on the Pitot-Static Test Set to achieve a pressure altitude of 12,000 feet. 18. Verify on the ATCRBS/Mode S Transponder Ramp Test Set that the transmitted pressure

altitude is 12,000 ± 125 feet. Record altitude readings. ATC-1 Observed Value: _______________ ATC-2 Observed Value: _______________

_______________________ ______________________




_______________________ ______________________


21. Vary the static pressure on the Pitot-Static Test Set to achieve a pressure altitude of 37,000.

22. Verify on the ATCRBS/Mode S Transponder Ramp Test Set that the transmitted pressure altitude is 37,000 ± 125 feet. Record altitude readings.


_______________________ ______________________


23. On the Flight ID/ATC/TCAS Control Panel, set the Function Select Mode Switch to “ALT OFF” position.

24. Verify on the ATCRBS/Mode S Transponder Ramp Test Set that no transmitted pressure

altitude is displayed. _______________________ ______________________





25. On the Pitot-Static Test Set, reduce the static pressure to achieve a pressure altitude of the field elevation at 29.92 Hg.

26. On Flight ID/ATC/TCAS Control Panel press “ALT” button, select switch to position “2” and

repeat step B.11 to B.25.

27. On Flight ID/ATC/TCAS Control Panel press “ALT” button to return to main ADC source.

28. Connect the Pitot-Static Test Set to the No.2 Air Data System per Boeing 737 AMM subject 34-11-01/501.

NOTE: FLOW RESTRICTORS, CONTROL VALVES, AND CUTOFF VALVES MUST BE CONTAINED IN THE AIR DATA TEST SET.

_______________________ ______________________


29. Apply static pressure to achieve a pressure altitude of 1,500 feet. Apply pitot pressure to achieve airspeed of 150 knots.

30. Using the ATCRBS/Mode S Transponder Ramp Test Set, interrogate the selected transponder

in the ATCRBS Reply Test mode. Verify the transmitted pressure altitude is 1,500 feet. Record altitude readings.




altitude is 3,000 feet. Record altitude readings. ATC-1 Observed Value: _______________ ATC-2 Observed Value: _______________

_______________________ ______________________



34. Verify on the ATCRBS/Mode S Transponder Ramp Test Set that the transmitted pressure altitude is 6,000 ±125 feet. Record altitude readings.


_______________________ ______________________







_______________________ ______________________




_______________________ ______________________


39. Vary the static pressure on the Pitot-Static Test Set to achieve a pressure altitude of 37,000.

40. Verify on the ATCRBS/Mode S Transponder Ramp Test Set that the transmitted pressure altitude is 37,000 ± 125 feet. Record altitude readings.


_______________________ ______________________


41. On the Flight ID/ATC/TCAS Control Panel, set the Function Select Mode Switch to “ALT OFF” position.

42. Verify on the ATCRBS/Mode S Transponder Ramp Test Set that no transmitted pressure

altitude is displayed. _______________________ ______________________


43. On the Pitot-Static Test Set, reduce the static pressure to achieve a pressure altitude of the field elevation at 29.92 Hg.

44. On Flight ID/ATC/TCAS Control Panel press “ALT” button, select switch to position “1” and

repeat step B.29 to B.43.

45. On Flight ID/ATC/TCAS Control Panel press “ALT” button to return to main ADC source.



C. ATC Mode-S #1 Parameter Test

a. Transponder Parameter Selection Test

1. On the Flight ID/ATC/TCAS Control Panel set the Transponder Select Switch to “1” and push the ATC IDENT push button.

2. Verify on the ATCRBS/Mode S Transponder Ramp Test Set that the transponder is transmitting

the Special Position Identification pulse and that it remains valid for 15 to 25 seconds. ID Pulse Duration Observed: ________ seconds


3. On the Flight ID/Transponder/TCAS Control Panel, rotate the concentric code selector knobs

from 0 through 7 for each digit of the Mode A identification code and verify the code is displayed correctly on the ATCRBS/Mode S Transponder Ramp Test Set.

NOTE: THE ATC CODE WILL BE DISPLAYED ON DIGITS THREE THRU SIX OF THE

FLIGHT ID/TRANSPONDER/TCAS CONTROL PANEL.

CAUTION: DO NOT SET THE ATC CODE TO EMERGENCY CODES 3100, 7500, 7600, 7700, OR 7777 WHEN PERFORMING ANY OF THE FOLLOWING TESTS. DOING SO MAY CAUSE EMERGENCY ALARMS IN THE AIR TRAFFIC CONTROL SYSTEM.

_______________________ ______________________


b. Mode-S Address Test

1. Access the “ATC Only All-Call Test” on the ATCRBS/Mode-S Transponder Ramp Test Set and interrogate the selected transponder.

2. Make sure the Mode-S transponder did not reply to the interrogation (Passed Test).

_______________________ ______________________

Accomplished By Inspected By 3. Interrogate selected transponder in the Mode S All Call format and verify on the Ramp Test Set

display that the transmitted Mode S Address is the same as the Mode S Address assigned to the aircraft. ATC-1 Address Observed: ____________

_______________________ ______________________


4. Interrogate the selected Mode-S transponder using the Invalid Address Test of the Ramp Test Set.



C. ATC Mode-S #1 Parameter Test Con’t

5. Make sure the Mode-S transponder did not reply to the interrogation (Passed Test). _______________________ ______________________


c. Reply Delay

1. Perform a Reply Delay Test and verify that the following parameters are within indicated range: Mode-S: 128 µs ± 0.25µs Observed Value: _____________ ITM A: 128 µs ± 0.25µs Observed Value: _____________ ITM C: 128 µs ± 0.25µs Observed Value: _____________ ATC A: 3.00 µs ± 0.50µs Observed Value: _____________ ATC C: 3.00 µs ± 0.50µs Observed Value: _____________

_______________________ ______________________


d. Reply Jitter

1. Perform a Reply Jitter Test and verify that reply jitter is within range as shown: ≤ 0.08 µs for Mode-S. ≤ 0.1 µs for ATC-A and ATC-C. ≤ 0.1 µs for ITM-A and ITM-C.

_______________________ ______________________


e. ATCRBS Reply Test

1. Perform an ATCRBS Reply Test and verify that following parameters are within range as shown:

F1 to F2 Spacing = 20.3 ± 0.1 µs F1 Pulse Width = 0.45 ± 0.1 µs F2 Pulse Width = 0.45 ± 0.1 µs

_______________________ ______________________





f. SLS Level

1. On the Ramp Test Set access the “SLS Level Test” page and interrogate the transponder. 2. Make sure the reply is received when the SLS pulse is –9 dB and no reply is received when the

SLS pulse is 0 dB.

NOTE: RUN THE SLS LEVEL TEST IN LESS THAN 95 FEET (28.96 METERS) OF THE UUT ANTENNA.


g. Reply Frequency Test

1. Interrogate the selected ATC system and verify the reply frequency of the transponder is 1090

MHz ± 1 MHz.

ATC Observed Frequency: _________________MHz _______________________ ______________________


h. SPR ON/OFF Test

1. On the Ramp Test Set ATC-601 access the “SPR ON/OFF TEST” page and interrogate the transponder.

2. Verify that a reply is received when SPR is ON and no reply is received when SPR is OFF.

_______________________ ______________________


i. Diversity Test 1. Move the test set to less than 50 feet from the top ATC antenna.

NOTE: MAKE SURE THE TOP ATC ANTENNA IS NOT IN THE LINE OF SIGHT OF THE

TEST SET ANTENNA. FOLLOW THE TEST SET OPERATOR’S GUIDE TO REDUCE MULTIPATH ERRORS. DO THE DIVERSITY TEST SEVERAL TIMES WITH THE TEST SET AT DIFFERENT LOCATIONS UNTIL YOU GET VALID RESULTS.

2. Push the SETUP key on the test set and enter the appropriate range for the top and bottom

antenna.

3. Set the “DIVERSITY TEST” page on the Ramp Test Set and interrogates the ATC Transponder.




4. Verify that power level difference is ≥ 20 dB. _______________________ ______________________


j. MTL Difference

1. Set the “MTL Difference Test” page on the Ramp Test Set and interrogate the ATC Transponder.

2. Verify the Minimum Threshold Level (MTL) difference between mode A and Mode C is ≤ 1.0

dB _______________________ ______________________


k. Transmit Power/Receiver Sensitivity

1. Move the Test Set antenna 6 feet vertically from the ground an in the line of sight of the ATC Bottom Antenna.

2. On the test set, push the SETUP key and select the bottom antenna.


TEST SET ANTENNA DURING THE POWER TEST.

3. Perform a power test and verify the peak power output of the transponder is between 51.0 dBm (125 watts) and 57.0 dBm (500 Watts).

ATC-1 Bottom Ant. Observed Power Output: ______________ dBm ATC-1 Top Ant. Observed Power Output: _________________ dBm

4. Verify the MTL of the transponder is –74 dBm ± 3dBm.

ATC-1 Bottom Ant. Observed MTL: ______________ dBm ATC-1 Top Ant. Observed MTL: _________________ dBm

5. Make sure the test shows PASSED for the BOT AVG (dBm).

_______________________ ______________________


6. Insert the antenna shield over the bottom ATC antenna.

7. Move the test set so that it is in the line of sight of the top ATC antenna.

8. Push the SETUP key on the test set. Enter the appropriate range for the top antenna and select the Top Antenna.



C. ATC Mode-S #1 Parameter Test Con’t 9. Repeat steps k.4 and k.5.

10. Make sure the test set shows PASSED for the Top AVG (dBm).

_______________________ ______________________


11. Remove shield from the ATC bottom antenna. l. Squitter Test

1. Set the “Squitter test” page on the Ramp Test Set and interrogate the ATC Transponder.

2. Verify that “Squitter Test-Passed” legend is shown in the Screen.

3. Make sure the Squitter’s period is between 0.8 to 1.2 seconds.

NOTE: IF THE TEST SET ANTENNA IS IN LIGHT OF SIGHT WITH ONLY ONE OF THE

ATC ANTENNAS, THE SQUITTER PERIOD WILL BE BETWEEN 1.6 TO 2.4 SECONDS.

_______________________ ______________________


m. Mode S Formats Test. 1. Set the “Mode S UF4 Test” on the Ramp Test Set and interrogate the ATC transponder.

Verify that the altitude reported in the replies to UF=4 are the same are the same reported on the “ATCRBS Reply Test” (refer to section C.g.).

Set the “Mode S UF5 Test” on the Ramp Test Set and interrogate the ATC transponder. _______________________ ______________________

Accomplished By Inspected By 2. Verify that the identity reported in the replies to UF=5, are the same that reported on the “Mode

S Address Test” (refer to section C.b).





n. ELS/EHS Test

This test is applicable to aircraft equipped with ATC Transponder Level 2 or upper. The following tests are to be conducted with an IFR ATC-601 Test set with capability to decode the Elementary and Enhanced Surveillance DF17 data.

NOTE: LEVEL 1 TRANSPONDER DOES NOT REPLY TO THIS TEST. FAILURE TO REPLY TO THIS TEST DOES NOT FAIL MODE-S IN AUTO TEST.

1. Flight ID

1. Put the test set antenna at a convenient bearing and distance from the antennas under test.

NOTE: THE TEST SET ANTENNA MUST BE WITHIN THE LINE OF SIGHT OF THE ATC

ANTENNAS.

2. Put the Test Set antenna in position towards the airplane antenna. 3. On the Flight ID/ATC/TCAS Control Panel press ATC/FID Selector Switch until FID light

comes ON.

4. On the Flight ID/ATC/TCAS Control Panel enter a Flight ID number using the left knob.

5. Set the ATC Ramp Test Set ATC-601 to show the “Flight ID Test” page and interrogate the ATC Transponder.

6. Verify that the Flight ID number entered on the Flight ID/ATC/TCAS Control Panel is the same

reported by the ATC Transponder.


2. Selected Vertical Intent Report Test

1. Set the MCP selected altitude to 25000 feet. 2. Set the FMS selected altitude to 30000 feet.

3. Set the baro correction on the barometric altimeter to 29.92 in Hg.

4. If the MCP allows it, set the ALT HOLD MODE to “ON” the VNAV Mode to “ON” and the

APPR MODE to “OFF”.

5. Set the Ramp Test Set IFR 601 test set to show the “Selected Vert Intent Report. Part1” page and interrogate the ATC transponders.




6. Verify the following parameters are reported as indicated:

MCP/FCU SEL ALT = 25000 ± 100 feet. FMS SEL ALT = N/A SOURCE INFO = NO TARGET ALT = “UNKNOWN”

_______________________ ______________________


7. Set the Ramp Test Set IFR 601 test set to show the “Selected Vert Intent Report. Part 2” page and interrogate the ATC transponders.


BARO PRESSURE ALT = 1013 mb VNAV MODE = N/ACTIVE APPR MODE = N/ACTIVE ALT HOLD MODE = N/ACTIVE MODE INFO = NO

_______________________ ______________________


3. Data Link Capability Report

1. Set the Ramp Test Set to show the “Data Link Capability Report, Page 1” page. Interrogate the ATC transponder.


SUBNET VER NBR = 0 XPNDR LEVEL= 2 - 4 SPECIFIC SER CAP REP FIELD = YES DTE = NO UELM SEG CAP = NO UELM CONT FLAG = NO

_______________________ ______________________





C. ATC Mode-S #1 Parameter Test Con’t 4. Verify the following parameters are reported as indicated:

DELM SEG CAP = NO DELM AIRCRAFT ID CAP = YES SI CAP = YES SQUITTER CAP = YES/NO* (Don’t Care) COMM USE GICB REP = YES/NO or 1/0* (Don’t Care)

NOTE: *RESULTS OF THIS TEST ARE NOT CONSIDERED CRITICAL.

_______________________ ______________________


4. Track and Turn Report

1. Set the EFIS displays to show the aircraft’s True Track angle. 2. Align all Inertial Reference Units and wait at least 30 minutes in order to get stable readings

during this test. 3. Connect the Air Data Test Set to the air data system No.2, and simulate an indicated airspeed of

200 Knots and an altitude of 10000 feet. 4. Set the Ramp Test Set IFR 601 to show the “Track and Turn Report” page and interrogate the

ATC transponder. 5. Verify the following parameters are reported as indicated:

ROLL ANGLE = 0.0 ± 2.0 degrees RATE = N/A T_TRACK ANGLE = Aircraft angle ± 2.0 degrees T_AIRSPEED = 240 ± 2.0 KTS GND SPEED = 0.0 ± 2.0 KTS

_______________________ ______________________


5. Heading and Speed Report

1. Connect the Air Data Test Set to the air data system No.1 and simulate an indicated airspeed of 250 knots and a climb rate of 1000fpm.

2. Set the Ramp Test Set IFR 601 to show the “Heading and Speed Report” page and interrogate

the ATC Transponder.





IND AIR SPEED = EFIS Indication ± 10%. Observed Value: ____________ MACH = EFIS Indication ± 0.01. Observed Value: ____________ BARO ALT RATE = Vert. Speed Indication ± 10%. Observed Value: ____________ MAG HDG = EFIS Indication ± 0.01. Observed Value: ____________ I_V_VEL = Climb rate ± 25 ft/min. Observed Value: ____________

_______________________ ______________________




D. ATC Mode-S #2 Parameter Test

a. Transponder Parameter Selection Test

1. On the Flight ID/ATC/TCAS Control Panel set the Transponder Select Switch to “R” and push the ATC IDENT push button.

2. Verify on the ATCRBS/Mode S Transponder Ramp Test Set that the transponder is transmitting

the Special Position Identification pulse and that it remains valid for 15 to 25 seconds. ID Pulse Duration Observed: ________ seconds


3. On the Flight ID/ATC/TCAS Control Panel, rotate the concentric code selector knobs from 0 through 7 for each digit of the Mode A identification code and verify the code is displayed correctly on the ATCRBS/Mode S Transponder Ramp Test Set.

NOTE: THE ATC CODE WILL BE DISPLAYED ON DIGITS THREE THRU SIX OF THE

FLIGHT ID/ATC/TCAS CONTROL PANEL.

CAUTION: DO NOT SET THE ATC CODE TO EMERGENCY CODES 3100, 7500, 7600, 7700, OR 7777 WHEN PERFORMING ANY OF THE FOLLOWING TESTS. DOING SO MAY CAUSE EMERGENCY ALARMS IN THE AIR TRAFFIC CONTROL SYSTEM.

_______________________ ______________________


b. Mode-S Address Test

1. Access the “ATC Only All-Call Test” on the ATCRBS/Mode-S Transponder Ramp Test Set and interrogate the selected transponder.



D. ATC Mode-S #2 Parameter Test Con’t



3. Interrogate selected transponder in the Mode S All Call format and verify on the Ramp Test Set

display that the transmitted Mode S Address is the same as the Mode S Address assigned to the aircraft.

Right ATC Address Observed: ___________

_______________________ ______________________


4. Interrogate the selected Mode-S transponder using the Invalid Address Test of the Ramp Test Set.


_______________________ ______________________


c. Reply Delay

1. Perform a Reply Delay Test and verify that the following parameters are within indicated range: Mode-S: 128 µs ± 0.25µs Observed Value: _____________ ITM A: 128 µs ± 0.25µs Observed Value: _____________ ITM C: 128 µs ± 0.25µs Observed Value: _____________ ATC A: 3.00 µs ± 0.50µs Observed Value: _____________ ATC C: 3.00 µs ± 0.50µs Observed Value: _____________

_______________________ ______________________


d. Reply Jitter

1. Perform a Reply Jitter Test and verify that reply jitter is within range as shown: ≤ 0.08 µs for Mode-S. ≤ 0.1 µs for ATC-A and ATC-C. ≤ 0.1 µs for ITM-A and ITM-C.

_______________________ ______________________





e. ATCRBS Reply Test

1. Perform an ATCRBS Reply Test and verify that following parameters are within range as shown:

F1 to F2 Spacing = 20.3 ± 0.1 µs F1 Pulse Width = 0.45 ± 0.1 µs F2 Pulse Width = 0.45 ± 0.1 µs

_______________________ ______________________


f. SLS Level

1. On the Ramp Test Set access the “SLS Level Test” page and interrogate the transponder.

2. Make sure the reply is received when the SLS pulse is –9 dB and no reply is received when the SLS pulse is 0 dB. Note: Run the SLS Level test in less than 95 feet (28.96 meters) of the UUT antenna.


g. Reply Frequency Test

1. Interrogate the selected ATC system and verify the reply frequency of the transponder is 1090 MHz ± 1 MHz.

ATC-2 Observed Frequency: _________________MHz

_______________________ ______________________


h. SPR ON/OFF Test

1. On the Ramp Test Set ATC-601 access the “SPR ON/OFF TEST” page and interrogate the transponder.

2. Verify that a reply is received when SPR is ON and no reply is received when SPR is OFF.

_______________________ ______________________





i. Diversity Test 1. Move the test set to less than 50 feet from the top ATC antenna.


TEST SET ANTENNA. FOLLOW THE TEST SET OPERATOR’S GUIDE TO REDUCE MULTIPATH ERRORS. DO THE DIVERSITY TEST SEVERAL TIMES WITH THE TEST SET AT DIFFERENT LOCATIONS UNTIL YOU GET VALID RESULTS.

2. Push the SETUP key on the test set and enter the appropriate range for the top and bottom

antenna.

3. Set the “DIVERSITY TEST” page on the Ramp Test Set and interrogate the ATC Transponder.

4. Verify that power level difference is ≥ 20 dB.


j. MTL Difference

1. Set the “MTL Difference Test” page on the Ramp Test Set and interrogates the ATC Transponder.

2. Verify the Minimum Threshold Level (MTL) difference between mode A and Mode C is ≤ 1.0

dB _______________________ ______________________


k. Transmit Power/Receiver Sensitivity

1. Move the Test Set antenna 6 feet vertically from the ground an in the line of sight of the ATC Bottom Antenna.

2. On the test set, push the SETUP key and select the bottom antenna.

Note: Make sure the top ATC antenna is not in the line of sight of the test set antenna during the Power test.

3. Perform a power test and verify the peak power output of the transponder is between 51.0 dBm (125 watts) and 57.0 dBm (500 Watts).

ATC-2 Bottom Ant. Observed Power Output: ______________ dBm ATC-2 Top Ant. Observed Power Output: _________________ dBm

4. Verify the MTL of the transponder is –74 dBm ± 3dBm.




ATC-2 Bottom Ant. Observed MTL: ______________ dBm ATC-2 Top Ant. Observed MTL: _________________ dBm

5. Make sure the test shows PASSED for the BOT AVG (dBm).

_______________________ ______________________


6. Insert the antenna shield over the bottom ATC antenna.

7. Move the test set so that it is in the line of sight of the top ATC antenna. 8. Push the SETUP key on the test set. Enter the appropriate range for the top antenna and select

the Top Antenna.

9. Repeat steps k.4 and k.5.

10. Make sure the test set shows PASSED for the Top AVG (dBm). _______________________ ______________________


11. Remove shield from the ATC bottom antenna. l. Squitter Test.

1. Set the “Squitter Test” Page on the Ramp Test Set and interrogate the ATC Transponder. 2. Verify That “Squitter Test-Passed” legend is shown in the Screen.

3. Make sure the squitter's period is between 0.8 to 1.2 seconds.

NOTE: IF THE TEST SET ANTENNA IS IN LINE OF SIGHT WITH ONLY ONE OF THE

ATC ANTENNAS, THE SQUITTER PERIOD WILL BE BETWEEN 1.6 TO 2.4 SECONDS.

_______________________ ______________________


m. Mode S Formats Test.

1. Set the “Mode S UF4 Test” on the Ramp Test Set and interrogate the ATC transponder.

Verify that the altitude reported in the replies to UF=4 are the same are the same reported on the “ATCRBS Reply Test” (refer to section 15.g.).




2. Set the “Mode S UF5 Test” on the Ramp Test Set and interrogate the ATC transponder. Verify that the identity reported in the replies to UF=5, are the same that reported on the

“Mode S Address Test” (refer to section 15.b). _______________________ ______________________


n. ELS/EHS Test

This test is applicable to aircraft equipped with ATC Transponder Level 2 or upper. The following tests are to be conducted with an IFR ATC-601 Test set with capability to decode the Elementary and Enhanced Surveillance DF17 data.

NOTE: LEVEL 1 TRANSPONDER DOES NOT REPLY TO THIS TEST. FAILURE TO

REPLY TO THIS TEST DOES NOT FAIL MODE-S IN AUTO TEST.

1. Flight ID

1. On the Flight ID/ATC/TCAS Control Panel press ATC/FID Selector Switch until FID light comes ON.

2. On the Flight ID/ATC/TCAS Control Panel enter a Flight ID number using the left knob.

3. On the Flight ID/Transponder/TCAS Control Panel, set the Transponder Select Switch to “2”.

4. Set the ATC Ramp Test Set ATC-601 to show the “Flight ID Test” page and interrogate the

ATC Transponder.

5. Verify that the Flight ID number entered on the Flight ID/ATC/TCAS Control Panel is the same reported by the ATC Transponder.

_______________________ ______________________


2. Selected Vertical Intent Report Test

2. Set the MCP selected altitude to 25000 feet. 3. Set the FMS selected altitude to 30000 feet. 4. Set the baro correction on the barometric altimeter to 29.92 in Hg. 5. If the MCP allows it, set the A LT HOLD MODE to “ON” the VNAV Mode to “ON” and the

APPR MODE to “OFF”. 6. Set the Ramp Test Set IFR 601 test set to show the “Selected Vert Intent Report. Part1” page

and interrogate the ATC transponders.



D. ATC Mode-S #2 Parameter Test Con’t 7. Verify the following parameters are reported as indicated:

MCP/FCU SEL ALT = 25000 ± 100 feet. FMS SEL ALT = N/A SOURCE INFO = NO TARGET ALT = “UNKNOWN”

_______________________ ______________________


8. Set the Ramp Test Set IFR 601 test set to show the “Selected Vert Intent Report. Part 2” page and interrogate the ATC transponders.


BARO PRESSURE ALT = 1013 mb VNAV MODE = N/ACTIVE APPR MODE = N/ACTIVE ALT HOLD MODE = N/ACTIVE MODE INFO = NO

_______________________ ______________________


3. Data Link Capability Report



SUBNET VER NBR = 0 XPNDR LEVEL= 2 - 4 SPECIFIC SER CAP REP FIELD = YES DTE = NO UELM SEG CAP = NO UELM CONT FLAG = NO

_______________________ ______________________





D. ATC Mode-S #2 Parameter Test Con’t 4. Verify the following parameters are reported as indicated:

DELM SEG CAP = NO DELM AIRCRAFT ID CAP = YES SI CAP = YES SQUITTER CAP = YES/NO* (Don’t Care) COMM USE GICB REP = YES/NO or 1/0* (Don’t Care)

Note: *Results of this test are not considered critical.


4. Track and Turn Report 1. Set the EFIS displays to show the aircraft’s True Track angle. 2. Align all Inertial Reference Units and wait at least 30 minutes in order to get stable readings

during this test. 3. Connect the Air Data Test Set to the air data system No.2, and simulate an indicated airspeed of

200 Knots and an altitude of 10000 feet. 4. Set the Ramp Test Set IFR 601 to show the “Track and Turn Report” page and interrogate the

ATC transponder.


ROLL ANGLE = 0.0 ± 2.0 degrees RATE = N/A T_TRACK ANGLE = Aircraft angle ± 2.0 degrees T_AIRSPEED = 240 ± 2.0 KTS GND SPEED = 0.0 ± 2.0 KTS


5. Heading and Speed Report

1. Connect the Air Data Test Set to the air data system No.2, and simulate an indicated airspeed of 250 knots and a climb rate of 1000fpm.

2. Set the Ramp Test Set IFR 601 to show the “Heading and Speed Report” page and interrogate the ATC Transponder.


IND AIR SPEED = EFIS Indication ± 10%. Observed Value: ____________ MACH = EFIS Indication ± 0.01. Observed Value: ____________ BARO ALT RATE = Vert. Speed Indication ± 10%. Observed Value: ____________ MAG HDG = EFIS Indication ± 0.01. Observed Value: ____________ I_V_VEL = Climb Rate ± 25 ft/min. Observed Value: ____________

_______________________ ______________________




E. ATC Return the aircraft to its normal configuration.

1. On the Pitot-Static Test Set, reduce the static pressure to achieve a pressure altitude of the field elevation at 29.92 Hg. Disconnect the Test Set from the No. 1 and No.2 Air Data Systems.

2. Return all aircraft switches to their normal operating positions. 3. Verify that the transponders, TCAS and DME suppression bus is interconnected.




7. TEST TRACKING FORM

All items have been complied with and signed:

Test Performed By:

Test Inspected By:

Test Results Recorded By:

Test Witnessed By:

Test Dated:

Test Performed on Aircraft Serial No.:

Test Performed on A/C Registration No.:

stc authorization letter els b737-400 msn 25110 and msn ...b737-400 4. type (aircraft, engine,...

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