ALERT SERVICE BULLETIN
412-15-169 PSL 7000000142 18 December 2015
MODEL AFFECTED:
412EP
SUBJECT:
LCR 100 ATTITUDE HEADING REFERENCE UNIT (AHRU) P/N 145130-7000 and P/N 145130-7001 UPGRADE TO P/N 145130-7010.
HELICOPTERS AFFECTED:
Helicopters listed in Block A are affected by Part 1 and 2 of this bulletin. Helicopters listed in Block B are affected by Part 2 only. Helicopters serial number 37002 and subsequent (Production 412EPI) do not require accomplishment of Part 1. Block A: Serial numbers 36491, 36501, 36502, 36505, 36511, 36512, 36528 to 36648, 36650 to 36657 and 36659 to 36671. Block B: Serial numbers 36672, 36674 to 36680, 36685, 36687, 36689, 36691, 36693, 36695, 36697, 36699, 37003 and 37004. [Serial numbers 36674 to 36680, 36685, 36687, 36689, 36691, 36693, 36695, 36697 and 36699 will have the intent of Part 1 of this bulletin accomplished prior to delivery. [Serial numbers 36649, 36658, 36673, 36681 to 36684, 36686, 36688, 36690, 36692, 36694, 36696, 36698 and 36700 to 36999 will have the intent of Part 1 and 2 accomplished prior to delivery. Serial numbers 37002, 37005 and subsequent will have the intent of Part 2 of this bulletin accomplished prior to delivery.]
COMPLIANCE:
No later than 14 December 2018
ASB 412-15-169 Page 1 of 8 Approved for public release.
DESCRIPTION: Bell Helicopter is aware of a misalignment condition of the LCR 100 Attitude Heading Reference System (AHRS) that may occur as a result of voltage drop below 15 volts during engine start. This condition may degrade the ability to maintain safe control of the helicopter during takeoff, when the autopilots are engaged. This anomaly affects the helicopter serial numbers listed in the “Helicopters Affected” Block A and B except helicopters 37002 (Production EPI) and subsequent. Northrop Grumman LITEF GmbH has informed Bell Helicopter of another possible anomaly that can cause the analog output of the LCR-100 to freeze without setting the associated warning flags. This condition can affect the flight instruments and proper function of the Automatic Flight Control System (AFCS). Part 1 of this bulletin mandates the replacement the AHRS 3 Amps circuit breakers by 5 Amps circuit breakers. Helicopters 37002 (Production EPI) and subsequent do not require accomplishment of Part 1. Part 2 of this bulletin mandates the upgrade or replacement of the LCR 100 AHRU for all helicopters listed in the “Helicopters Affected” Blocks A and B. The affected LCR 100 AHRUs can be returned to Northrop Grumman LITEF GmbH or MASCO Service Corporation for upgrade. Accomplishment of Parts 1 and 2 as applicable constitutes the terminating action to the ASB 412-11-146 and ASB 412-15-162. Once this bulletin is accomplished, the Temporary Revisions BHT-412-FM-4 (TR-1), BHT-412-FM-4 (TR-2), and BHT-412FM-5 (TR-1) must be removed from the applicable Flight Manual. Accomplishment of Part 2 of this Service Directive meets the intent of LITEF Service Bulletin 145130-0017-845 and complies with the requirements of EASA AD 20150093. APPROVAL: The engineering design aspects of this bulletin are FAA approved. CONTACT INFO: For any questions regarding this bulletin, please contact: Bell Helicopter Product Support Engineering - Medium Helicopters Tel: 450-437-6201 / 1-800-363-8028 /
[email protected]
ASB 412-15-169 Page 2 of 8 Approved for public release.
MANPOWER: Approximately 3.0 man-hours for Part 1 and 2.0 man-hours for Part 2 are required to complete this bulletin. This estimate is based on hands-on time, and may vary with personnel and facilities available. WARRANTY: Owners/Operators of Bell helicopters who comply with the instructions in this bulletin will be eligible to receive labor and parts per the Material Section for Part 1, and labor only for Part 2 of this bulletin. Bell Helicopter has recently introduced enhancements to the VISTA Portal which allocates specific warranty entitlement for a helicopter by serial number. The Product Service Letter (PSL) number, which will be listed below the bulletin number on the introduction page, is going to be a required field when submitting a claim for labor. If you receive an ASB or TB that does not have a PSL number, then there is no warranty entitlement for that bulletin. Labor entitlement: Part 1 Part 2
$255.00USD $170.00USD
To receive Parts, and labor credit under warranty: • •
Comply with the instructions contained in this bulletin no later than the applicable date in the “Compliance Section”. If there is a PSL number identified in the bulletin, you will be required to enter this PSL number which will validate warranty entitlement for the selected helicopter. Please make sure that you use the Bulletin tab on the warranty section in VISTA to file your claim.
Note: Customers who fail to comply with the instructions in this bulletin before the compliance date will not be eligible for the special warranty listed above. 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
MS22073-5 16-001020 MS25036-149 NAS1149DN832J
Circuit Breaker EMI cover Terminal Washer
2 2 2 2
ASB 412-15-169 Page 3 of 8 Approved for public release.
Note 1 Note 1 Note 1 Note 1
Note 1:
Refer to the accomplishment instructions for required quantities according to helicopter serial number.
Consumable Material: None required. SPECIAL TOOLS: Part Number
Nomenclature
M22520/1-01 M22520/1-02
Crimper Turret head
Qty 1 1
WEIGHT AND BALANCE: No change. ELECTRICAL LOAD DATA: Not affected. REFERENCES: BHT-412-IPB, Illustrated Parts Breakdown BHT-412-MM, Maintenance Manual BHT-ELEC-SPM ASB 412-11-146 ASB 412-15-162 BHT-412-FM-4 (TR-1) BHT-412-FM-4 (TR-2) BHT-412-FM-5 (TR-1) Customizing Drawing 412-899-536 EASA AD No: 2015-0093 Northrop Grumman LITEF GmbH Service Bulletin No.: 145130-0017-845 Northrop Grumman LITEF GmbH Modification Process Flow Chart U.S Department of Commerce Form BIS-711 PUBLICATIONS AFFECTED: BHT-412-IPB, Illustrated Parts Breakdown BHT-412-FM-4 BHT-412-FM-5 Customizing Drawing 412-899-536
ASB 412-15-169 Page 4 of 8 Approved for public release.
ACCOMPLISHMENT INSTRUCTIONS: Part 1: Replacement of the AHRS circuit breakers. -NOTEPart 1 is applicable to helicopter serial numbers listed in the “Helicopters Affected” Block A only. Helicopter serial numbers 36491, 36501, 36502, 36505, 36511, and 36512 had the AHRUs LCR-100 installed by customizing drawing 412-899-536-101 before delivery. Part 1 can be accomplished either prior to or concurrently with Part 2 of this bulletin. 1. Prepare the helicopter for maintenance. 2. Make sure all electrical power is removed from the helicopter. 3. Disconnect the helicopter battery. 4. Access the right side and left side overhead console and locate the pilot and copilot AHRS circuit breakers reference designators 3407CB2 and 3407CB1. 5. Disconnect wires F119A22 and F117A22 from the pilot and copilot AHRS circuit breakers. 6. Remove the existing 3 amp pilot and copilot AHRS circuit breakers P/N MS22073-3. 7. Install the new 5 amp pilot and copilot AHRS circuit breakers P/N MS22073-5. 8. Connect wires F119A22 and F117A22 to the pilot and copilot AHRS circuit breakers. 9. Secure the right side and left side overhead console. 10. Reconnect the helicopter battery. 11. Carry out the AHRS functional test IAW BHT-412-MM, Chapter 97. 12. Make an entry in the helicopter logbook and historical service records indicating compliance with part A of this Alert Service Bulletin.
ASB 412-15-169 Page 5 of 8 Approved for public release.
Part 2: LCR 100 AHRUs upgrade. -NOTEPart 2 is applicable to all helicopter serial numbers listed in the “Helicopters Affected” Blocks A and B. 1. Prepare the helicopter for maintenance. 2. Make sure all electrical power is removed from the helicopter. 3. Disconnect the helicopter battery. 4. Access the aft left side avionic compartment and verify the LCR 100 AHRU part numbers on the data plate. 5. If the units are identified with P/N 145130-7010, do steps 11, 12, and 13. 6. If the units are identified with P/N 145130-7000 or P/N 145130-7001, follow the procedures in the following steps. 7. Contact Northrop Grumman LITEF GmbH or MASCO Service Corporation for return instructions of the LCR 100 AHRU P/N 145130-7000 or P/N 145130-7001. Refer to the attached Northrop Grumman LITEF GmbH Service Bulletin No. 145130-0017845. -NOTERefer to the attached Northrop Grumman LITEF GmbH flow chart for selecting the appropriate repair center; Northrop Grumman LITEF GmbH for Europe or MASCO Service Corporation for North America and all other countries. -NOTEThe LCR 100 AHRU P/N 145130-7010 units are subject to EAR control and require an export license. License applications may take several months to process. To minimize the impact on your operations, we recommend sending the attached form BIS-711 to Northrop Grumman LITEF GmbH or MASCO Service Corporation as soon as possible. The form BIS-711 must be signed in ink by the Purchaser if the Ultimate Consignee is not the same.
ASB 412-15-169 Page 6 of 8 Approved for public release.
8. Remove the LCR 100 AHRU P/N 145130-7000 or P/N 145130-7001 from the helicopter. 9. Send the LCR 100 AHRU to Northrop Grumman LITEF GmbH or MASCO Service Corporation for modification. 10. Upon receiving the replacement/upgraded LCR 100 AHRU P/N 145130-7010, do the following: a. Prepare the helicopter for maintenance. b. Make sure all electrical power is removed from the helicopter. c. Disconnect the helicopter battery. d. Install the LCR 100 AHRU P/N 145130-7010 in accordance with the BHT-412MM, Chapter 97. -NOTESerial numbers 37003 and 37004 will have the intent of sub steps e to h of this bulletin accomplished prior to delivery. e. Remove the existing terminal lug on the EMI cover P/N 16-001020 grounding wire. f. Install terminal lug P/N MS25036-149 onto the lanyard of the EMI cover P/N 16-001020. g. Secure the lanyard terminal lug with washer P/N NAS1149DN832J on the LCR 100 AHRU mounting rack using the existing screw. h. Install the new EMI cover P/N 16-001020 on connector J6 of the LCR 100 (Figure 1). i.
Re-connect the helicopter battery.
j.
Carry out the AHRS functional test IAW BHT-412-MM, Chapter 97.
11. Remove temporary revision (TR-1) and (TR-2) from the BHT-412-FM-4 or (TR-1) from the BHT-412-FM-5. 12. Return the helicopter to flight status. 13. Make an entry in helicopter historical service records indicating compliance with Part 2 of this Alert Service Bulletin.
ASB 412-15-169 Page 7 of 8 Approved for public release.
ASB 412-15-169 Page 8 of 8 Approved for public release.
Northrop Grumman LITEF GmbH
SERVICE BULLETIN No.: 145130-0017-845
Issue D
Frozen Analog Output after Processor BITE Failures
ATTITUDE and HEADING REFERENCE SYSTEM (AHRS) LCR-100 Part No. 145130-2000 145130-2001 145130-7000 145130-7001 145130-7100
ATA-Ref. 34-20 Originally issued: September 30, 2014
© 2014 NG LITEF GmbH, Freiburg This document contains proprietary information / know-how which is known only to a limited number of persons. Transfer and copying of this document, use or disclosure unless expressly authorized by NG LITEF is subject to damages. All rights reserved regarding patents and registered designs.
Northrop Grumman LITEF GmbH Loerracher Strasse 18 79115 FREIBURG GERMANY
Issue D April 1, 2015 Page 1 of 7
Northrop Grumman LITEF GmbH
SB 145130-0017-845
Issue D
LCR-100 Service Bulletin__________________________________________________
SUBJECT: Frozen Analog Output after Processor BITE Failures I. PLANNING INFORMATION A. Effectivity This Service Bulletin applies to NG LITEF LCR-100 Attitude and Heading Reference Units (AHRU) with the following Part Numbers:
145130-2000 145130-2001 145130-7000 145130-7001 145130-7100 SB 145130-0017-845, Issues A, B and C are superseded by this Issue D. B. Concurrent Requirements N/A
C. Reason Tests at NG LITEF laboratories discovered a problem, which can cause frozen Analog Output on the LCR-100 without setting the associated warning flags into warning status (System Warn, Attitude Warn, Heading Warn 1, Heading Warn 2, Turn Rate Warn, Yaw Rate Warn). The problem occurs if the Continuous BITE routine (CBIT) of the AHRU detects failures causing the system to switch into Reset Hold Mode (Silent Mode). In these cases, the digital output interfaces are no longer served, and the analog output voltages as well as the status of the warning discrete are no longer updated. The analog output data are frozen and the warning discrete may improperly indicate “valid”. WARNING: In this condition, the AHRS provides misleading information on the analog output. All digital ARINC 429 output channels of the AHRU stop transmitting data at the same time when the analog output freezes at the current value and Northrop Grumman LITEF GmbH Loerracher Strasse 18 79115 FREIBURG GERMANY
Issue D April 1, 2015 Page 2 of 7
Northrop Grumman LITEF GmbH
SB 145130-0017-845
Issue D
LCR-100 Service Bulletin__________________________________________________ flag status. This means the fault status of the system is visible to the pilot if digital Electronic Flight Instruments (e.g. EFIS) are installed. The described fault condition can be cleared during operation by resetting the power to the AHRU (e.g. pulling and resetting of circuit breakers).
D. Description of Remedy For the affected LCR-100 versions, the Synchro Interface Module (Electronic Board) inside the AHRU is modified. An additional watchdog circuit is implemented to the Synchro Interface Module, which runs out if the software stops triggering it. After the watchdog runs out the output discrete relays on the Synchro Interface Module (Attitude Warn, Heading Warn 1, Heading Warn 2, Turn Rate Warn) will fall into the status ”WARN / INVALID” and the analog output is set to zero voltage. The Yaw Rate Warn Discrete and the System Warn Discrete are not corrected by the modification. A change of software is not required.
E. Compliance TC and STC holders are requested to assess the criticality of this fault condition to the aircraft’s safety depending on the use of analogue output and the presence of comparison of analogue data in the installation. TC and STC holders are requested to inform the operators accordingly. If the flight safety is affected this Service Bulletin is mandatory. For further information and assistance, please contact NG LITEF.
F. Approval The modification is a minor change in the TSO/ETSO certified LCR-100 AHRS PN mentioned in paragraph I.B. under the authority of the EASA approval No. AP234, Issue 3, 5 October 2012.
G. Manpower Effected LCR-100 AHRU has to be replaced in the aircraft. Required manpower depends on accessibility of the AHRU in the aircraft.
Northrop Grumman LITEF GmbH Loerracher Strasse 18 79115 FREIBURG GERMANY
Issue D April 1, 2015 Page 3 of 7
Northrop Grumman LITEF GmbH
SB 145130-0017-845
Issue D
LCR-100 Service Bulletin__________________________________________________
H. Dimensions, Weight and Balance Impact on AHRU mechanical interface: Impact on weight and balance:
None Negligible
I. Electrical Load Data N/A
J. Software Accomplishment Summary N/A
K. Reference Service Bulletin 145130-0017-845
Issues A, B and C
L. Other Publications Affected LCR-100 Declaration of Design and Performance LCR-100 System Specification LCR-100 Installation and Maintenance Instructions LCR-100 System Safety Assessment
Northrop Grumman LITEF GmbH Loerracher Strasse 18 79115 FREIBURG GERMANY
145130-0010-100 145130-0000-312 145130-0000-840 145130-0010-545
Issue D April 1, 2015 Page 4 of 7
Northrop Grumman LITEF GmbH
SB 145130-0017-845
Issue D
LCR-100 Service Bulletin__________________________________________________
M. Interchangeability and Identification After the modification, the LCR-100 AHRUs will get new Part Numbers as follows: Pre Modification
Post Modification
145130-2000 145130-2001 145130-7000 145130-7001 145130-7100
145130-2010 145130-2011 145130-7010 145130-7011 145130-7110
Attention: Attention of operators of AHRUs with MOD status 16, 18 and 19 is directed to the following. The synchro output voltages for pitch and roll signals are reduced to 85% (measured at 15 kOhm) after the modification. The heading synchro values and the 2-wire output voltage levels remain unchanged. The voltage reduction keeps the values within required tolerances also if the outputs are not connected to a low impedance synchro receiver but to a high impedance (15 kOhm) input device. The lower output voltage is a fit, form and function replacement in ARINC 407 synchro applications since the indicated angle of synchro outputs is defined by the ratio between the three synchro voltages independent of the absolute value of these voltages. For AHRU with MOD status 20 and higher the synchro output voltages remain at the same level.
Northrop Grumman LITEF GmbH Loerracher Strasse 18 79115 FREIBURG GERMANY
Issue D April 1, 2015 Page 5 of 7
Northrop Grumman LITEF GmbH
SB 145130-0017-845
Issue D
LCR-100 Service Bulletin__________________________________________________ II. MATERIAL INFORMATION A. Availability The Hardware Modification for units in service is available by May 1, 2015. Customers are requested to contact NG LITEF for planning of modification activities. B. Warranty The warranty is not affected. C. Service Contact Information Address all requests or correspondence to: Northrop Grumman LITEF GmbH Customer Service Commercial Avionics Loerracher Str. 18 79115 Freiburg Germany Phone +49 (761) 4901-142 Fax +49 (761) 4901-773 Email:
[email protected] D. Repair Centers The modification can be performed at one of the following repair centers Northrop Grumman LITEF GmbH Loerracher Str. 18 79115 Freiburg Germany Phone +49 (761) 4901-142 Fax +49 (761) 4901-773 Email:
[email protected] MASCO Service Corporation 850 S. Dooley St. Grapevine, TX 76051 USA Phone: +1 (817) 481-8205 FAX: +1 (817) 488-8918 Email:
[email protected] The capability for hardware modification at MASCO Service Corporation is scheduled to be available from August 1, 2015. Northrop Grumman LITEF GmbH Loerracher Strasse 18 79115 FREIBURG GERMANY
Issue D April 1, 2015 Page 6 of 7
Northrop Grumman LITEF GmbH
SB 145130-0017-845
Issue D
LCR-100 Service Bulletin__________________________________________________
III. Accomplishment Instructions for Operators A. Modification For the modification, the AHRU must be removed from the aircraft and returned to a repair station mentioned in paragraph II.D. B. Aircraft Wiring Check If the analog output signals are used for Primary Flight Displays (PFD) or Flight Control Systems (FCS) the appropriate warning discrete output on the Synchro Interface Module must be used. Caution: The System Warn discrete on connector J4 Pins 21/15/42 must not be used as sole information for signal validity to PFD and FCS. Customers and Operators are requested to check the aircraft wiring for correct usage of the warning discretes. The table below defines the correct usage of warning discretes for validity of analog output signals. Signal 3 wire Pitch Synchro Output 3 wire Roll Synchro Output 2 wire Pitch AC 200 (167) mV/deg 2 wire Roll AC 200 (167) mV/deg 2 wire Pitch AC 50 mV/deg 2 wire Roll AC 50 mV/deg 3 wire Heading Synchro Output 1 3 wire Heading Synchro Output 2 Turn Rate DC output Yaw Rate DC output Normal Acceleration DC Output
Northrop Grumman LITEF GmbH Loerracher Strasse 18 79115 FREIBURG GERMANY
Connector Pins J3 - 11/26/40 J3 - 10/25/39 J3 - 09/24 J3 - 07/22 J3 - 08/23 J3 - 06/21 J3 - 13/28/42 J3 - 12/27/41 J3 - 15/30/43 J3 - 14/29/44 J3 - 37/38
Related Warning Discrete Attitude Warn Discrete Attitude Warn Discrete Attitude Warn Discrete Attitude Warn Discrete Attitude Warn Discrete Attitude Warn Discrete Heading Warn Discrete 1 Heading Warn Discrete 2 Turn Rate Warn Discrete Yaw Rate Warn Discrete System Warn Discrete
Connector Pins J3 - 03/18 J3 - 03/18 J3 - 03/18 J3 - 03/18 J3 - 03/18 J3 - 03/18 J3 - 32/17 J3 - 16/01 J3 - 02/31 J4 - 41/61 J4 - 21/15/42
Issue D April 1, 2015 Page 7 of 7
FORM BIS-711 FORM APPROVED UNDER OMB CONTROL NO. 0694-0021, 0694-0093
U.S. DEPARTMENT OF COMMERCE BUREAU OF INDUSTRY AND SECURITY
DATE RECEIVED (Leave Blank)
Information furnished herewith is subject to the provisions of Section 12(c) of the Export Administration Act of 1979, as amended, 50 U.S.C. app 2411(c) and its unauthorized disclosure is prohibited by law.
STATEMENT BY ULTIMATE CONSIGNEE AND PURCHASER 1. ULTIMATE CONSIGNEE
CITY
ADDRESS LINE 1
COUNTRY
ADDRESS LINE 2
POSTAL CODE
TELEPHONE OR FAX
2. DISPOSITION OR USE OF ITEMS BY ULTIMATE CONSIGNEE NAMED IN BLOCK 1 We certify that the items: (left mouse click in the appropriate box below)
A. B. C. D. E.
Ƒ Ƒ Ƒ Ƒ Ƒ
Will be used by us (as capital equipment) in the form in which received in a manufacturing process in the country named in Block 1 and will not be reexported or incorporated into an end product. Will be processed or incorporated by us into the following product (s) _____________________________________________________________ to be manufactured in the country named in Block 1 for distribution in _____________________________________________________________ Will be resold by us in the form in which received in the country named in Block 1 for use or consumption therein. The specific end-use by my customer will be_________________________________________________________________________________ Will be reexported by us in the form in which received to _______________________________________________________________________ Other (describe fully)___________________________________________________________________________________________________
NOTE: If BOX (D) is checked, acceptance of this form by the Bureau of Industry and Security as a supporting document for license applications shall not be construed as an authorization to reexport the items to which the form applies unless specific approval has been obtained from the Bureau of Industry and Security for such export.
3. NATURE OF BUSINESS OF ULTIMATE CONSIGNEE NAMED IN BLOCK 1 A. The nature of our usual business is__________________________________________________________________________________________________ B. Our business relationship with the U.S. exporter is _____________________________________________________________________________________ and we have had this business relationship for ____ year(s). 4. ADDITIONAL INFORMATION 5. ASSISTANCE IN PREPARING STATEMENT STATEMENT OF ULTIMATE CONSIGNEE AND PURCHASER We certify that all of the facts contained in this statement are true and correct to the best of our knowledge and we do not know of any additional facts which are inconsistent with the above statement. We shall promptly send a supplemental statement to the U.S. Exporter, disclosing any change of facts or intentions set forth in this statement which occurs after the statement has been prepared and forwarded, except as specifically authorized by the U.S. Export Administration Regulations (15 CFR parts 730-774), or by prior written approval of the Bureau of Industry and Security, we will not reexport, resell, or otherwise dispose of any items approved on a license supported by this statement (1) to any country not approved for export as brought to our attention by means of a bill of lading, commercial invoice, or any other means, or(2) to any person if we know that it will result directly or indirectly, in disposition of the items contrary to the representations made in this statement or contrary to Export Administration Regulations.
6. SIGNATURE OF OFFICIAL OF ULTIMATE CONSIGNEE
7. NAME OF PURCHASER
NAME OF OFFICIAL TITLE OF OFFICIAL DATE (mmmm,dd,yyyy)
SIGNATURE OF PURCHASER NAME OF OFFICIAL TITLE OF OFFICIAL DATE (mmmm,dd,yyyy)
CERTIFICATION FOR USE OF U.S. EXPORTER - We certify that no corrections, additions, or alterations were made on this form by us after the form was signed by the (ultimate consignee)(purchaser). 8. NAME OF EXPORTER
SIGNATURE OF PERSON AUTHORIZED TO CERTIFY FOR EXPORTER
NAME OF PERSON SIGNING THIS DOCUMENT
TITLE OF PERSON SIGNING THIS DOCUMENT
DATE (mmmm,dd,yyyy)
We acknowledge that the making of any false statements or concealment of any material fact in connection with this statement may result in imprisonment or fine, or both and denial, in whole or in part, of participation in U.S. exports and reexports. Public reporting burden for this collection of information is estimated to average 15 minutes per response plus one minute for recordkeeping, including the time for reviewing instruments, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden, to the Director of Administration, Room 3889, Bureau of Industry and Security, U.S. Department of Commerce,
Washington, DC 20230, and to the Office of Management and Budget Paperwork Reduction Project (06940021, 0694-0093), Washington, D.C. 20503. Notwithstanding any other provision of law, no person is obligated to respond to nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the Paperwork Reduction Act unless that collection of information displays a currently valid OMB Control Number.
EASA AD No.: 2015-0093
EASA
AIRWORTHINESS DIRECTIVE AD No.: 2015-0093
Date: 27 May 2015 Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Community, its Member States and of the European third countries that participate in the activities of EASA under Article 66 of that Regulation. This AD is issued in accordance with EU 748/2012, Part 21.A.3B. In accordance with EU 1321/2014 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate an aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agency [EU 1321/2014 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption].
Design Approval Holder’s Name:
Type/Model designation(s):
NORTHROP GRUMMAN LITEF GmbH
LCR-100 Attitude Heading Reference System
ETSO Authorisation: EASA.21O.855 Rev. A Foreign AD:
Not applicable
Supersedure:
None
ATA 34
Navigation – Attitude Heading Reference System – Modification / Replacement
Manufacturer(s):
Northrop Grumman LITEF GmbH, formerly LITEF GmbH
Applicability:
Northrop Grumman LITEF GmbH LCR-100 Attitude Heading Reference System (AHRS), Part Number (P/N) 145130-2000, P/N 145130-2001, P/N 145130-7000, P/N 145130-7001 and P/N 145130-7100. These AHRS units are known to be installed on, but not limited to, Pilatus PC-12, Learjet 31A, Cessna 560XL, RUAG (Dornier) 228 series, and PZL Mielec M28 (Sky Truck) aeroplanes; and Bell Helicopter Textron Inc. 412EP, Bell Helicopter Textron Canada 407, and Sikorsky S-76C helicopters.
Reason:
During laboratory tests of LCR-100 AHRS units, it was discovered that when BITE (built-in test) detects failures causing the system to switch into Reset Hold Mode (Silent Mode), system reset was not correctly generated. This reset failure induces frozen analogue output data (Attitude and Heading) without detection or warning to the pilot, while the digital A429 output data is indicated invalid and remains invalid. For aircraft installations using LCR-100 analogue data, there may be misleading analogue output provided by the equipment to the aircraft (pilot and autopilot). The A429 digital Attitude and Heading data is indicated invalid, and is therefore unavailable, but not misleading to the aircraft. Unless a system reset is performed by a switch OFF / switch ON sequence, the unit remains in this failure mode. However, depending on aircraft installation, if there is no automatic comparison of analogue output (e.g. with another equipment output) to detect unit failure, this condition, if not corrected, could lead to undetected attitude and heading errors, possibly resulting in loss of control of the aircraft.
TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
1/3
EASA AD No.: 2015-0093
To address this potential unsafe condition, Northrop Grumman LITEF issued Service Bulletin (SB) 145130-0017-845 (now at issue C), providing instructions for the affected units to be removed and replaced with modified units. For the reasons described above, this AD requires removal from service of the affected LCR-100 AHRS units and replacement with modified (new P/N) units. In addition, as an interim measure pending AHRS unit replacement, for aircraft installations using the analogue output without the means to automatically detect the misleading data, this AD requires a temporary amendment of the applicable Aircraft Flight Manual (AFM). Effective Date:
10 June 2015
Required Action(s) and Compliance Time(s):
Required as indicated, unless accomplished previously: (1) For aircraft installations using the LCR-100 analogue output (see Note 1) without automatic detection of the frozen output data of the AHRS, within 30 days after the effective date of this AD, amend the AFM of the aircraft by inserting a Temporary Revision (TR) to the AFM (Supplement), provided by the design approval (TC) holder of the affected aircraft, or the design change approval (STC) holder of the modification through which the LCR-100 unit was installed, as applicable. The AFM(S) TR must include the following: -
information explaining the safety issue,
-
instructions for the pilot to closely monitor the Attitude and Heading information to detect frozen data,
-
instructions for the pilot to accomplish after detection (considering possible reset, diversion, etc.), as applicable to the aircraft installation, and
-
limitations or procedures, as deemed necessary to ensure safe flight.
Note 1: Aircraft installations using the LCR-100 analogue output only for nonsafety critical functions are not affected by the requirements of paragraph (1) of this AD. (2) Within the compliance time specified in Table 1 of this AD, as applicable, modify the aircraft by replacing each AHRS unit having a P/N specified as ‘old’ in Table 2 of this AD with a modified unit, having a P/N specified as ‘new’ in Table 2 of this AD. This modification must be accomplished in accordance with approved aeroplane modification instructions provided by the TC holder of the affected aircraft, or the STC holder of the modification through which the LCR-100 unit was installed. Northrop Grumman LITEF SB 145130-0017-845 contains the necessary instructions how to have a unit modified. Table 1 – Modification Affected aircraft installations
Compliance Time
Using the LCR-100 analogue output without automatic detection of the frozen output data of the AHRS
6 months
All other installations, including those defined in Note 1 of this AD
24 months
TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
2/3
EASA AD No.: 2015-0093
Table 2 – LCR-100 AHRS P/N old and new P/N old
P/N new
145130-2000
145130-2010
145130-2001
145130-2011
145130-7000
145130-7010
145130-7001
145130-7011
145130-7100
145130-7110
(3) Concurrent with modification of an aircraft as required by paragraph (2) of this AD, the AFM change, if required by paragraph (1) of this AD (see Note 1 of this AD), can be removed from that aircraft. (4) Do not install on any aircraft a LCR-100 AHRS unit, having a P/N specified as ‘old’ in Table 1 of this AD, as required by paragraph (4.1) or (4.2) of this AD, as applicable. (4.1) For an aircraft with LCR-100 AHRS installed, having a P/N specified as ‘old’ in Table 1 of this AD: After modification as required by paragraph (2) of this AD. (4.2) For an aircraft with LCR-100 AHRS installed, having a P/N listed as ‘new’ in Table 1 of this AD, or with a AHRS installed with a P/N not listed in Table 1 of this AD: From the effective date of this AD. Ref. Publications:
Northrop Grumman LITEF SB 145130-0017-845, issue C, dated 14 January 2015, or issue D, dated 1 April 2015, which can be downloaded from the NG LITEF GmbH website. The use of later approved revisions of this document is acceptable for compliance with the requirements of this AD.
Remarks:
1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 04 March 2015 as PAD 15-020 for consultation until 01 April 2015. The Comment Response Document can be found at http://ad.easa.europa.eu/. 3. Enquiries regarding this AD should be referred to the Safety Information Section, Certification Directorate, EASA. E-mail:
[email protected]. 4. For any question concerning the technical content of the requirements in this AD, please contact: Northrop Grumman LITEF GmbH, Customer Service Commercial Avionics, Loerracher Str. 18, 79115 Freiburg, Germany Telephone +49 (761) 4901-142 , Fax +49 (761) 4901-773 Email:
[email protected].
TE.CAP.00110-004 © European Aviation Safety Agency. All rights reserved. Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
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