Federal Register of Legislation - Australian Government

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AD/RAD/76 Amdt 1 Airworthiness Directives/Pt 107 — Equipment as made
Honeywell Primus II RNZ-850 or -851 Integrated Navigation Units
Administered by: Infrastructure and Transport
Exempt from sunsetting by the Legislative Instruments Act 2003 s 54(2) item 9
Registered 16 May 2007
Tabling HistoryDate
Tabled HR21-May-2007
Tabled Senate12-Jun-2007
Date of repeal 03 May 2010
Repealed by CASA ADCX 005/10 - Revocation of Airworthiness Directives

 

AIRWORTHINESS DIRECTIVE

On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/RAD/76 and issues the following AD under subregulation 39.001(1) of CASR 1998.  The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

Radio Communication and Navigation Equipment

AD/RAD/76 Amdt 1

Honeywell Primus II RNZ-850 or
-851 Integrated Navigation Units

6/2007

 

Applicability:

Honeywell Primus II RNZ-850(  ) or -851(  ) Integrated Navigation Units (INU) with a part number (P/N) from the following range:

 

       7510100-811 through 7510100-814 inclusive
7510100-831 through 7510100-834 inclusive
7510100-901 through 7510100-904 inclusive
7510100-911 through 7510100-914 inclusive
7510100-921 through 7510100-924 inclusive
7510100-931 through 7510100-934 inclusive

 

Note 1:  RNZ-850(  ) or -851(  ) units are know to be fitted to, but not limited to, the following series of aircraft:

 

       BAE Systems (Operations) Limited (Jetstream) Model 4101
Bombardier BD-700-1A10 and CL-215-6B11 (CL415 variant)
Cessna Model 560, 560XL and 650
Dassault Model Mystère-Falcon 50
AvCraft Dornier Model 328-100 and -300
Embraer Model EMB-135 and EMB-145series
Learjet Model 45
Raytheon Model Hawker 800XP and Hawker 1000
Sikorsky Model S-76A, S-76B and S-76C

Requirement:

1.    If not previously accomplished in accordance with the original issue of this Directive (AD/RAD/76), perform a one-time general visual inspection of the modification plate for the NV-850 Navigation Receiver Module (NRM) P/N 7510134-811, -831, -901 or -931, which is part of the RNZ-850(  ) or -851(  ) INU; to determine if Mod "L" has been incorporated.

 

The modification plate, which is located on the bottom of the RNZ-850(  ) or -851(  ) unit, is labelled NV-850 and contains the P/N together with the serial number for the NV-850 NRM, if Mod "L" is incorporated, the letter "L" will be blacked out.  Honeywell Alert Service Bulletin (ASB) 7510100-34-A0035, dated 11 July 2003, is an acceptable source of service information for this inspection.

 

 

 

If Mod "L" is not incorporated, no further action is necessary in accordance with this Requirement.

 

Note 2:  For the purposes of this Amendment, a general visual inspection is defined as: "A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity.  This level of inspection is made from within touching distance unless otherwise specified.  A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area.  This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors.  Stands, ladders, or platforms may be required to gain proximity to the area being checked."

 

Note 3:  For more information on the inspection specified in Requirement 1, refer to Honeywell Technical Newsletter A23-3850-001, Revision 1, dated 21 January 2003.

 

2.    If, following the Requirement 1 inspection, Mod "L" is determined to be incorporated, revise the limitations section of the Aircraft Flight Manual (AFM) to include the following statements, this may be accomplished by inserting a copy of this Directive into the AFM:

 

“Flight Limitations

When crossing the Outer Marker on glideslope, the altitude must be verified with the value on the published procedure.

For aircraft with a single operating glideslope receiver, the approach may be flown using normal procedures no lower than Localizer Only Minimum Descent Altitude (MDA).

For aircraft with two operating glideslope receivers, the aircraft may be flown to the published minimums for the approach using normal procedures if both glideslope receivers are tuned to the approach and both crewmembers are monitoring the approach using independent data and displays.

 

3.    Honeywell Primus II NV-850 Navigation Receiver Modules, with Mod "L" incorporated, may not be fitted to any Honeywell Primus II RNZ-850 or -851 Integrated Navigation Unit on any aircraft as a replacement part, unless the Requirement 2 AFM revision is accomplished.

 

4.    For aircraft on which Mod “L” was found to be installed during the Requirement 1 inspection or for aircraft whose Aircraft Flight Manual (AFM) Limitations Section was revised in accordance with the original issue of AD/RAD/76 - Perform an inspection of the modification plate on the NV-850 NRM; part number 7510134-811, -831, -901, or -931; which is part of the RNZ-850(  ) or
-851(  ) INU; to determine if Mod L, N, P, R or T is installed.”

 

 

The modification plate located on the bottom of the RNZ-850(  ) or-851(  ) INU is labelled NV-850 and contains the P/N and serial number for the NV-850 NRM.  If Mod L, N, P, R or T is installed, the corresponding letter on the modification plate will be blacked out.  ASB 7510100-34-A0035 is an acceptable source of service information for this inspection.

 

If Mod T is installed, no further action is necessary in accordance with this Requirement and the AFM revision inserted in accordance with the original issue of AD/RAD/76 or Requirement 2 of this Amendment may be removed.

 

5.    If Mod L, N, P, or R is installed, carry out applicable related investigative and corrective, together with other specified actions, in accordance with the Accomplishment Instructions of ASB 7510100-34-A0035 and Honeywell Service Bulletin (SB) 7510100-34-0037, dated 8 July 2004; to ensure that the NRM is at the Mod T configuration.

 

Note 4:  ASB 7510100-34-A0035, refers to Honeywell ASB 7510100-34-A0034, dated 28 February 2003, as an additional source of service information for inspecting to determine the NRM part number, marking the modification plates of the NRM and INU accordingly, testing the INU for discrepant signals, and replacing the unit with a new or modified INU, as applicable.  ASB 7510100-34-A0034 refers to Honeywell ASB 7510134-34-A0016, currently at Revision 001, dated 4 March 2003, as an additional source of service information for marking the modification plates of the NRM and INU.

 

Note 5:  SB 7510100-34-0037 refers to Honeywell SB 7510134-34-0018, dated
8 July 2004, as an additional source of service information for modifying the NRM to the Mod T configuration.

 

6.    Remove the AFM revision inserted in accordance with the original issue of AD/RAD/76 or Requirement 2 of this Amendment.

 

Note 6:  FAA AD 2006-22-05 Amdt 39-14802 refers.

Compliance:

For Requirement 1 - Within 30 days after the effective date of this Amendment.

 

For Requirement 2 - Before further flight after the Requirement 1 inspection.

 

For Requirement 3 - As of the effective date of this Amendment.

 

For Requirement 4 - Within 24 months after the effective date of this Amendment.

 

For Requirement 5 - Before further flight after the Requirement 4 inspection.

 

For Requirement 6 - Following accomplishment of Requirement 5.

 

 

This Amendment becomes effective on 7 June 2007.

Background:

The United States Federal Aviation Administration has advised of receiving reports indicating that erroneous glideslope indications have occurred on Empresa Brasileira de Aeronautica S.A. (Embraer) Model EMB-145 series airplanes.  In these incidents, the glideslope deviation indicator unexpectedly changed from a centred position to a hard-fly-down or hard-fly-up indication during an instrument landing system (ILS) approach.  These incidents have been attributed to discrepancies of certain Honeywell Primus II NV-850 NRM that are part of the Honeywell Primus II RNZ-850 or -851 Integrated Navigation Units installed on the affected aeroplanes.  An affected navigation receiver module may produce an erroneous glideslope deviation indication when operating in a narrow range of cold temperatures with the glideslope receiver tuned to certain frequencies.  An erroneous glideslope deviation indication could lead to the aircraft making an approach off the glideslope, which could result in impact with an obstacle or terrain.

 

The original issue of this Directive required a visual inspection to determine the modification status of the receiver module and, if necessary, the revision of the AFM.  These actions were considered interim and further rulemaking was anticipated.

 

This Amendment, whilst continuing the requirements of the original issue, introduces additional inspections to identify the NRM modification status and, if necessary, modification of the NRM.  At the same time t also allows removal of the AFM temporary revision.  The Amendment also extends the list of possible affected aircraft and corrects minor typographical errors.

 

The original issue of this Directive became effective on 11 March 2003.


David Punshon
Delegate of the Civil Aviation Safety Authority

27 April 2007