safety assessment report

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Issue: A Date: 08 April 2021

Equipment/Furnishings Passenger Compartment

Inspection / Storage / Replacement

Instructions for 511959, 513766 and 514518 Electronics Module Assemblies (EMA).

Part 25 and Part 23 Aircraft Affected

Issued By:

AmSafe, Inc.

1043 N. 47th Avenue Phoenix, Arizona 85043

Telephone: +1(602) 850-2850 Fax: +1(602) 850-2812

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Transmittal Sheet TO: Holders of SB514518-25-01, Issue A, dated April 08, 2021. This page transmits issue A to

SB514518-25-01.

A complete reissue of SB514518-25-01 accomplishes the changes summarized below. Remove and replace SB514518-25-01.

Page(s) Correction/Update 4, 5 13 19

Updated Section C for Compliance and D for Reason. Updated Section 2. Updated Section a); Added note after section C; Deleted Section 7.

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Record of Revisions

Retain this record at the front of the service bulletin. On receipt of a revision record the incorporation of the revision on this sheet.

Issue No.

Issue Date

Date Inserted By

Issue No.

Issue Date

Date Inserted By

- Nov. 17, 2020

A April. 08, 2021

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Planning Information A. Effectivity This service bulletin provides inspection criteria for the AmSafe Electronics Module Assembly (EMA) for part numbers 511959-( )-( ), 513766-( )-( ), and 514518-( )-( ).

Table 1 EMA P/N 511959-401-42 511959-403-50 511959-405-58 511959-407-42 511959-409-50 511959-411-58 511959-413-42 513766-401-42 513766-403-50 513766-405-58 514518-401-58

B. Classification Article manufacturer’s recommendation. C. Compliance Mandatory if the aircraft has been subjected to extended storage in environmentally uncontrolled conditions, then Guideline 2 (Section 2) must be completed. D. Reason The impacts of COVID-19 to aircraft are resulting in unanticipated operational conditions. AmSafe has observed an increase in the occurrence of returned of EMAs from stored or parked aircraft. EMAs installed on stored or parked aircraft are subjected to non-operational conditions, where the duration of storage and environmental conditions are unknown. Some returned EMAs have exhibited a drained battery condition, the cause of which has not yet been established. This SB is focused on the EMA part numbers listed in Table 1 only and does not apply to other variants. Please refer to Table 1 above or contact AmSafe customer service for any clarification.

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AmSafe is investigating the potential impacts of parked or stored aircraft to the EMA through industry data and in-house testing. The AmSafe EMA controls the function of the airbag and contains Energizer L91 lithium batteries. Manufacturer data provided by Energizer indicates that the L91 battery will sustain up to 95% capacity (shelf life) for twenty years at 21C (70F). While Energizer indicates that the battery can withstand temperatures between -40C (-40F) and 60C (140F), battery life is significantly impacted at elevated temperatures. Energizer shared that a decrease in battery shelf life will roughly double for every 10C above 21C (the baseline condition). Fielded batteries in normal operating conditions with constant power draw have a calculated service life of ten years at 21C (70F), roughly half of the calculated shelf life. The Energizer data indicates that battery shelf life may be reduced to less than 1.5 years when exposed to prolonged storage at temperatures of 81C (178F) or more. An EMA in service for several years, followed by exposure to elevated temperatures (such as a parked or stored aircraft) can expect to have failed batteries or an abbreviated service life. These EMA’s should be considered for expedited replacement. Extended exposure to high humidity has also been shown to have a negative impact to service life of EMA electronics, and potentially drains batteries. Chafed cables or damaged push to test buttons have resulted in drained batteries in past instances. These EMAs should be evaluated and considered for replacement. Please reference Service Letter SL511438 for inspection of potential damage. All EMA’s that have been installed in aircraft that have been in storage as per “C” above must have a diagnostic check per Guideline 2 (Section 2) before the aircraft returns to service. AmSafe recommends removal and replacement of EMAs on aircraft having been stored, parked, or temporarily removed from service under environmentally uncontrolled conditions. Contact AmSafe customer service for return options.

E. Description This bulletin provides instructions for inspection, storage and removal of EMAs (as depicted in table 1 above). Detailed instructions for EMA removal and diagnostic check can be found in the instructions for continued airworthiness (ICA) / component maintenance manual (CMM) of respective part numbers. F. Approval This service bulletin contains no modification information that revises the approved configuration and therefore does not require Federal Aviation Administration (FAA) or other regulatory agency approval. G. Manpower

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The time to complete Guideline 1 is no more than 20 minutes. The time to complete Guideline 2 is no more than 5 minutes. H. Warranty NA I. Material Cost and Availability For returns or replacement, contact AmSafe customer service for more information or RMA number. Purchase orders should contain the following information:

Part Number Quantity Name of Airline / Operator Shipping Address

After receiving an RMA number, return units to: AmSafe, Inc. 1043 N 47th Avenue Phoenix, Arizona 85043 Telephone: +1(602) 850-2850 Fax: +1(602) 850-2812

J. Tooling Cost and Availability None. K. Weight and Balance There is no affect to weight as a result of the actions defined within this service bulletin. L. Electrical Load Data None. M. Software Accomplishment Summary None. N. References

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Original ICA / CMM instructions for each part number. O. Other Publications Affected None.

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Accomplishment Instructions Storing the Aircraft: Operators should follow Guideline 1 Returning Stored Aircraft to Service: Operators should follow Guideline 2 1. Guidelines for EMAs when storing aircraft (applies to aircraft which have not yet been

parked or stored). If the aircraft has been parked or stored, refer to Guideline 2. 1a. Personnel and Equipment

a) Trained personnel should perform testing and fault isolation 1b. Remove the EMA (205).

WARNING: ENSURE THE INFLATABLE CONNECTOR HALF ASSEMBLY AND THE INFLATABLE

BUCKLE HALF ASSEMBLY ARE UNBUCKLED FOR EACH SEAT POSITION AND REMAIN SEPARATED TO MINIMIZE THE POTENTIAL OF INJURY TO PEOPLE OR DAMAGE TO EQUIPMENT IN THE EVENT OF AN UNINTENTIONAL AIRBAG DEPLOYMENT.

WARNING: ALWAYS DISCONNECT THE FEMALE P2, P3 AND P4 CONNECTORS ON THE INTERFACE CABLE ASSEMBLY (190) FOR EACH SEAT POSITION PRIOR TO ANY COMPONENT REPLACEMENT OR ELECTRICAL OR MECHANICAL SEAT MAINTENANCE.

WARNING: DO NOT REMOVE THE EMA FROM THE MOUNTING BRACKET UNTIL THE CABLE ASSEMBLY HAS BEEN DISCONNECTED (190)

WARNING: DO NOT DROP OR MISHANDLE THE EMA (205). DAMAGE TO THE ELECTRONICS, BATTERY OR SENSOR MAY OCCUR. IF THE EMA (205) IS DROPPED OR DAMAGED THERE IS POTENTIAL FOR AN ANOMALY, SUCH AS NOT FUNCTIONING AS INTENDED OR DESIGNED. A DAMAGED OR MISHANDLED EMA (205) COULD RESULT IN INJURY TO PEOPLE OR DAMAGE TO EQUIPMENT IF INSTALLED ON THE SEAT.

WARNING: IF DAMAGE OR MISHANDLING OCCURRED OR IS SUSPECTED, DO NOT RE-INSTALL THE EMA (205). RETURN THE EMA (205) TO AMSAFE FOR REPLACEMENT.

a) Disconnect the P2, P3, P4 connectors as applicable (Refer to Figure 5). Unlock connectors by sliding the red tab backwards. Press down on the yellow tab and gently pull connectors apart.

b) Unscrew the thumb screws on the interface cable assembly (190), Figure 1.

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Figure 1. Representative Interface Cable Assembly (190) Connection to the EMA (205)

c) Pull the interface cable assembly (190) out straight. d) Cover the exposed interface cable connector to prevent damage and protect against

dirt. e) Remove the four fasteners on the EMA (205) and remove the EMA (205) from the

mounting bracket.

1c. Store the EMA in a dry, environmentally controlled location -40C (-40F) and 60C (140F).

1d. Re-Installation of the EMA after Storage

a) Before installing the EMA after storage, check the EMA service life. b) Check the DOM on the EMA label (Figure 2).

Thumb Screws

190

205

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Figure 2. Representative Labels on EMA

c) Remove and replace the EMA upon: 1) Expiration of the service life (the total sum of storage life and installation life,

not to exceed 10 years calculated from the DOM). 2) A maximum storage period of 10 years calculated from the DOM.

Properly dispose the EMA If steps 1 or 2 apply. d) Install the EMA after storage (205).

WARNING: IN THE CASE OF A SYSTEM DEPLOYMENT, DO NOT USE ANY SEAT OR

MONUMENT WITH A SYSTEM SHARING THE SAME EMA AS THE DEPLOYED SYSTEM. REMOVE AND RETURN ALL COMPONENTS TO AMSAFE.

WARNING: DO NOT CONNECT THE INTERFACE CABLE ASSEMBLY (190) UNTIL THE EMA (205) IS INSTALLED IN THE MOUNTING BRACKET.

WARNING: DO NOT DROP OR MISHANDLE THE EMA (205). DAMAGE TO THE ELECTRONICS, BATTERY OR SENSOR MAY OCCUR. IF THE EMA (205) IS DROPPED OR DAMAGED THERE IS POTENTIAL FOR AN ANOMALY, SUCH AS NOT FUNCTIONING AS INTENDED OR DESIGNED. A DAMAGED OR MISHANDLED EMA (205) COULD INJURE PEOPLE OR DAMAGE EQUIPMENT IF INSTALLED ON THE SEAT. IF DAMAGE OR MISHANDLING OCCURRED OR IS SUSPECTED, DO NOT INSTALL THE EMA (205). RETURN THE EMA (205) TO AMSAFE FOR REPLACEMENT.

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WARNING: ENSURE THE EMA (205) IS SECURE TO THE SEAT AND THE SEAT IS SECURELY MOUNTED TO THE AIRCRAFT STRUCTURE TO PREVENT UNINTENTIONAL DEPLOYMENT OF THE AIRBAG THAT MAY INJURE PEOPLE OR DAMAGE EQUIPMENT.

WARNING: THE LAST ELECTRICAL CONNECTION IS TO THE P2 CONNECTOR ON THE INTERFACE CABLE ASSEMBLY. THIS CONNECTION IS MADE ONLY AFTER REPLACEMENT OF ALL COMPONENTS.

e) Orient the EMA (205) aircraft forward (Figure 3) and install the EMA (205) to the mounting bracket or seat structure using four fasteners.

f) Torque fasteners 30±2 in-lb.

Figure 3. Representative EMA (205) Aircraft Forward Orientation

g) Reconnect the interface cable assembly by carefully inserting the cable connector into the EMA and tightening the two thumb screws (Ref Figure 1).

h) Connect each P2, P3, P4 connector as applicable on the cable assembly interface (190) (Figure 4) to the P1 connector on the connector subassembly (from the inflatable connector half assembly (20)). Lock connectors by sliding the red tab forward (Figure 5). The red tab will not engage unless connectors are fully seated.

205

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Figure 4 – Inflatable Connector Half Assembly (20) and Cable Assembly, Interface (190) Connection

Figure 5 – Male P1 and Female P2 Connectors - Locked Position

i) Run a system diagnostic check. For Push-To-Test (PTT) refer to instructions listed in Guideline 2.

Connectors

190

20

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2. Guidelines for EMA’s installed on aircraft that have been stored or parked under

environmentally uncontrolled conditions, and where the duration of storage and environmental conditions are unknown. 2a. Perform PTT check for EMA P/Ns 511959 & 514518 (Single inflator per PAX)

a) Personnel and Equipment

1) Trained personnel should perform testing and fault isolation 2) No equipment or materials are required to perform the PTT procedure

b) System diagnostics are performed manually via a push-to-test (PTT) procedure.

WARNING: DO NOT PERFORM A FUNCTIONAL TEST WHEN THE AIRCRAFT IS AIRBORNE

WARNING: ENSURE THE EMA IS SECURED TO THE EMA BRACKET. DO NOT PERFORM A PTT IF THE EMA IS NOT SECURED IN THE EMA BRACKET; THE SYSTEM MAY INADVERTENTLY DEPLOY AND MAY INJURE PEOPLE OR DAMAGE EQUIPMENT.

WARNING: WHEN REPLACING/RETESTING THE EMA, DO NOT TEST AN EMA THAT IS NOT

SECURED IN THE EMA BRACKET. INADVERTANT SYSTEM DEPLOYMENT MAY OCCUR.

c) Ensure all electrical connections on the following components are secure. 1) EMA 2) Interface cable assembly 3) Inflator assembly

d) Ensure the EMA is secured in the EMA bracket.

e) Find the LEDs on the EMA (Figure 6). There is one LED for the EMA and three LEDs for up to three seat positions (one LED per seat position).

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Figure 6. Representative EMA

f) Push the PTT button (Figure 7).

Figure 7. PTT Button

g) Get diagnostic test results (Figure 8).

NOTE: Results are displayed for only 6 seconds before the EMA automatically performs (step a. If you did not see the results, wait until the LEDs are no longer lit and retest.

Seat 1 LED

EMA/Wireless LED Seat 3 LED Seat 2 LED

1 2 3 EMA

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Figure 8. Diagnostic Results

1) The test passed if passing results were obtained. The EMA automatically performs step 3).

2) The test failed if passing results were not obtained. The EMA automatically performs step a.

a. If the failure is indicated by no illumination of the EMA LED or a red EMA LED, do not use the EMA. Remove and replace the EMA and return the EMA to AmSafe

b. For any other failure, refer to the testing and fault isolation section of the CMM.

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3) The EMA automatically runs a pairing routine for wireless diagnostics (Figure

9). a. If passing results were obtained, testing is complete. b. The EMA failed if passing results were not obtained. c. If the failure is indicated by no illumination of the EMA LED or a red EMA

LED, do not use the EMA. Remove and replace the EMA and return the EMA to AmSafe

d. For any other failure, refer to the testing and fault isolation section of the CMM.

Figure 9. Pairing Routine

2b. Perform PTT check for EMA P/N 513766 (Dual inflator per PAX)

a) Personnel and Equipment 1) Trained personnel should perform testing and fault isolation. 2) No equipment or materials are required to perform the PTT procedure.

b) PTT - Dual Inflator System

WARNINGS: DO NOT PERFORM A FUNCTIONAL TEST WHEN THE AIRCRAFT IS AIRBORNE.

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WARNINGS: ENSURE THE EMA IS SECURED TO THE EMA BRACKET. DO NOT PERFORM A PTT IF THE EMA IS NOT SECURED IN THE EMA BRACKET; THE SYSTEM MAY INADVERTENTLY DEPLOY AND MAY INJURE PERSONNEL OR DAMAGE EQUIPMENT.

WARNINGS: WHEN REPLACING/RETESTING THE EMA, DO NOT TEST AN EMA THAT IS NOT

SECURED IN THE EMA BRACKET. INADVERTENT SYSTEM DEPLOYMENT MAY OCCUR.

1) Perform an Inspection/Check. 2) Ensure all electrical connections on the following components are secure.

a. EMA. b. Cable assembly, interface and LRU inflator cable interface. c. Inflator assemblies.

3) Ensure the EMA is secured in the EMA bracket. 4) Find the LEDs on the EMA. There is one LED for the EMA and two LEDs for

the inflator assemblies (one LED per inflator assembly) (Figure 10).

Figure 10 – EMA

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5) Push the PTT button (Figure 11).

Figure 11 – PTT Button

6) Get test results (Figure 12).

Note: Results are displayed for only 6 seconds before the EMA automatically performs a pairing routine as noted below. If you did not see the results, wait until the LEDs are no longer lit and retest.

Figure 12 – Diagnostic Results

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a. The test passed if passing results were obtained. The test failed if passing results were not obtained.

b. If the failure is indicated by no illumination of the EMA LED or a red EMA LED, do not use the EMA. Remove and replace the EMA and return the EMA to AmSafe

c. For any other failure, refer to the testing and fault isolation section of the CMM.

Note: The EMA will automatically run a pairing routine for wirless diagnotics (Figure 13). The wirless pairing test result is not required for functional check of the EMA.

Figure 13 – Pairing Routine

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