2003-04-06: Modification Plate for the Honeywell Primus II NV850 Navigation Receiver Module

2003-04-06 Various Aircraft: Amendment 39-13054. Docket 2003-NM-41-AD. Applicability: Aircraft, certificated in any category, equipped with a Honeywell Primus II RNZ-850/-851 Integrated Navigation Unit having a part number identified in Table 1 of this AD; including, but not limited to BAE Systems (Operations) Limited (Jetstream) Model 4101 airplanes; Bombardier BD-700-1A10 series airplanes; Bombardier CL-215-6B11 (CL415 variant) series airplanes; Cessna Model 560, 560XL, and 650 airplanes; Dassault Model Mystere-Falcon 50 series airplanes; Dornier Model 328-100 and -300 series airplanes; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 and -145 series airplanes; Learjet Model 45 airplanes; Raytheon Model Hawker 800XP and Hawker 1000 airplanes; and Sikorsky Model S-76A, S-76B, and S-76C aircraft. Table 1 of this AD follows: Table 1.-Integrated Navigation Unit Part Numbers Part numbers 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: This AD applies to Honeywell Primus II RNZ-850/-851 Integrated Navigation Units installed on any aircraft, regardless of whether the aircraft has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For aircraft that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (e) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To ensure that the flightcrew has an accurate glideslope deviation indication, accomplish the following: Compliance Time for Action (a) Within 5 days after the effective date of this AD, accomplish the requirements of either paragraph (b) or (c) of this AD. Inspection To Determine Part Number (b) Perform a one-time general visual inspection of the modification plate for the Honeywell Primus II NV-850 Navigation Receiver Module; part number 7510134-811, -831, -901, or -931; which is part of the Honeywell Primus II RNZ-850/-851 Integrated Navigation Unit; to determine if Mod "L" has been installed. The modification plate is located on the bottom of the Honeywell Primus II RNZ-850/-851 Integrated Navigation Unit, is labeled NV-850, and contains the part number and serial number for the Honeywell Primus II NV-850 Navigation Receiver Module. If Mod "L" is installed, the letter "L" will be blacked out. (1) If Mod "L" is installed, before further flight, do paragraph (c) of this AD. (2) If Mod "L" is not installed, no further action is required by this paragraph. Note 2: For the purposes of this AD, 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 paragraph (b) of this AD, refer to Honeywell Technical Newsletter A23-3850-001, Revision1, dated January 21, 2003. Aircraft Flight Manual Revision (c) Revise the Limitations section of the aircraft flight manual (AFM) to include the following statements (which may be accomplished by inserting a copy of the AD 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 crew members are monitoring the approach using independent data and displays. Parts Installation (d) As of the effective date of this AD, no person may install a Honeywell Primus II NV-850 Navigation Receiver Module on which Mod "L" has been installed, on the Honeywell Primus II RNZ-850/-851 Integrated Navigation Unit of any airplane, unless paragraph (c) of this AD is accomplished. Alternative Methods of Compliance (e) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA. Operators shall submit their requests through an appropriate FAA Principal Maintenance or Operations Inspector, as applicable, who may add comments and then send it to the Manager, Los Angeles ACO. Note 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO. Special Flight Permits (f) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. Effective Date (g) This amendment becomes effective on March 11, 2003.