Airworthiness Directives; Various Aircraft Equipped With Honeywell Primus II RNZ-850( )/-851( ) Integrated Navigation Units, 62907-62910 [E6-17658]

Download as PDF Federal Register / Vol. 71, No. 208 / Friday, October 27, 2006 / Rules and Regulations DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20080; Directorate Identifier 2003–NM–193–AD; Amendment 39–14802; AD 2006–22–05] RIN 2120–AA64 Airworthiness Directives; Various Aircraft Equipped With Honeywell Primus II RNZ–850( )/–851( ) Integrated Navigation Units Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. rmajette on PROD1PC67 with RULES1 AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which applies to various aircraft equipped with certain Honeywell Primus II RNZ–850( )/–851( ) integrated navigation units (INUs). That AD, as one alternative for compliance, provides for a one-time inspection to determine whether a certain modification has been installed on the Honeywell Primus II NV–850 navigation receiver module (NRM), which is part of the INU. In lieu of accomplishing this inspection, and for aircraft found to have an affected NRM, the existing AD provides for revising the aircraft flight manual to include new limitations for instrument landing system approaches. This new AD requires inspecting to determine whether certain modifications have been done on the NRM; and doing related investigative, corrective, and other specified actions, as applicable; as well as further modifications to address additional anomalies. This AD results from reports indicating that erroneous glideslope indications have occurred on certain aircraft equipped with the subject INUs. We are issuing this AD to ensure that the flightcrew has an accurate glideslope deviation indication. 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. DATES: This AD becomes effective December 1, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of December 1, 2006. ADDRESSES: You may examine the AD docket on the Internet at https:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street VerDate Aug<31>2005 14:48 Oct 26, 2006 Jkt 211001 SW., Nassif Building, Room PL–401, Washington, DC. Go to https://pubs.cas.honeywell.com or contact Honeywell International, Inc., Commercial Electronic Systems, 21111 North 19th Avenue, Phoenix, Arizona 85027–2708, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: J. Kirk Baker, Aerospace Engineer, Systems and Equipment Branch, ANM– 130L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone (562) 627–5345; fax (562) 627–5210. SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at https://dms.dot.gov or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the street address stated in the ADDRESSES section. Discussion The FAA issued a supplemental notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 2003–04–06, amendment 39–13054 (68 FR 8539, February 24, 2003). The existing AD applies to various aircraft equipped with certain Honeywell Primus II RNZ– 850/–851 integrated navigation units (INUs). That supplemental NPRM was published in the Federal Register on May 18, 2006 (71 FR 28827). That supplemental NPRM proposed to continue to require inspecting to determine whether certain modifications have been done on the NRM; and doing related investigative, corrective, and other specified actions, as applicable; as well as further modifications to address additional anomalies. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received from the single commenter. Request To Clarify Reply to Comment to Original NPRM The commenter, Air Wisconsin, has requested an explanation of our reply to its comment to the original NPRM. The original comment requested clarification of the proposed requirements for inspecting to determine the PO 00000 Frm 00033 Fmt 4700 Sfmt 4700 62907 modification level of the NRM and proposed that paragraph (k) of the original NPRM be revised to state that paragraph (j) of the AD need not be performed under certain conditions. The commenter asserts that our reply to that original comment was contradictory and confusing because we stated that we had made no change to paragraph (k) of the original NPRM when, in fact, paragraph (k) of the supplemental NPRM had been changed. We acknowledge the commenter’s concern. As stated in our original reply, we determined that paragraph (j) of the AD is required regardless of compliance time or the findings of paragraph (f); this is because paragraph (j) requires inspecting for Mod N, P, R, or T, as well as Mod L. Therefore, we did not change paragraph (k) of the original NPRM as the commenter suggested. However, we determined that paragraph (k) was incorrect in that it stated that paragraph (f) did not need to be done if paragraph (j) was accomplished within the compliance time specified by paragraph (f). Paragraph (f) of the AD deals with compliance times and has no findings, while paragraph (g) of the AD requires an inspection and has findings. Therefore, it was our intent to revise paragraph (k) to read as it appears in the supplemental NPRM; that is, if paragraph (j) is accomplished within the compliance time specified by paragraph (f), paragraph (g) does not need to be done. We have made no further changes to paragraph (k) of the AD in this regard. Explanation of Change To Applicability We have revised the applicability of the AD to identify model designations as published in the most recent type certificate data sheet for the affected models. Clarification of INU References The applicability of the supplemental NPRM specifies that the AD applies to aircraft ‘‘equipped with a Honeywell Primus II RNZ–850/–851 INU having a part number identified in Table 1 of this AD.’’ However, the Honeywell service bulletins identified in the following table variously refer to ‘‘–850/–851,’’ ‘‘–850/A/B/C,’’ ‘‘–851/A/B/C,’’ and ‘‘–850(X)/–851(X)’’ INUs, indicating that the RNZ–850/–851 part number might or might not contain a suffix letter. Although the service bulletins identified in the following table make it clear that the INU part numbers, as identified in Table 1 of the AD, are the primary identifiers of all affected INUs, we have determined that these various suffix references could cause confusion. Therefore, to address all references to suffix letters in the service bulletins, we E:\FR\FM\27OCR1.SGM 27OCR1 62908 Federal Register / Vol. 71, No. 208 / Friday, October 27, 2006 / Rules and Regulations have revised the AD to read ‘‘–850( )/– 851( )’’ where applicable. HONEYWELL SERVICE INFORMATION Honeywell Revision level Alert Service Bulletin 7510100–34–A0034 ........................................................................................................ Alert Service Bulletin 7510100–34–A0035 ........................................................................................................ Alert Service Bulletin 7510134–34–A0016 ........................................................................................................ Service Bulletin 7510134–34–0018 ................................................................................................................... Service Bulletin 7510100–34–0037 ................................................................................................................... Original .... Original .... 001 ........... Original .... Original .... Conclusion We have carefully reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We have determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance For the purposes of this AD, we estimate that there are 3,063 aircraft worldwide that may be equipped with a part that is subject to this AD, including about 1,500 aircraft of U.S. registry. The inspection to determine whether Mod L has been done, which is currently required by AD 2003–04–06 and retained in this AD, will take about 1 work hour per aircraft, at an average labor rate of $80 per work hour. Based on these figures, the estimated cost of the currently required actions is $80 per aircraft. rmajette on PROD1PC67 with RULES1 Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. VerDate Aug<31>2005 14:48 Oct 26, 2006 Jkt 211001 Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing amendment 39–13054 (68 FR 8539, February 24, 2003) and adding the following new airworthiness directive (AD): I 2006–22–05 Various Aircraft: Amendment 39–14802. Docket No. FAA–2005–20080; Directorate Identifier 2003–NM–193–AD. PO 00000 Frm 00034 Fmt 4700 Sfmt 4700 Date February 28, 2003. July 11, 2003. March 4, 2003. July 8, 2004. July 8, 2004. Effective Date (a) This AD becomes effective December 1, 2006. Affected ADs (b) This AD supersedes AD 2003–04–06. Applicability (c) This AD applies to aircraft, certificated in any category, equipped with a Honeywell Primus II RNZ–850( )/–851( ) integrated navigation unit (INU) 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 Model BD–700–1A10 series airplanes; Model Bombardier CL–215–6B11 (CL–415 variant) series airplanes; Cessna Model 560, 560XL, and 650 airplanes; Dassault Model Mystere-Falcon 50 series airplanes; AvCraft Dornier Model 328–100 and –300 series airplanes; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB–135 airplanes and Model EMB–145, –145ER, –145MR, –145LR, –145XR, –145MP, and –145EP 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.—INU PART NUMBERS Part Nos. 7510100–811 sive. 7510100–831 sive. 7510100–901 sive. 7510100–911 sive. 7510100–921 sive. 7510100–931 sive. through 7510100–814 incluthrough 7510100–834 incluthrough 7510100–904 incluthrough 7510100–914 incluthrough 7510100–924 incluthrough 7510100–934 inclu- Note 1: This AD applies to Honeywell Primus II RNZ–850( )/–851( ) INUs 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 (m) of this AD. The request should include an assessment of the effect of the E:\FR\FM\27OCR1.SGM 27OCR1 Federal Register / Vol. 71, No. 208 / Friday, October 27, 2006 / Rules and Regulations 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. Unsafe Condition (d) This AD results from reports indicating that erroneous glideslope indications have occurred on certain aircraft equipped with the subject INUs. We are issuing this AD to ensure that the flightcrew has an accurate glideslope deviation indication. 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. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Requirements of AD 2003–04–06 rmajette on PROD1PC67 with RULES1 Compliance Time For Action (f) Within 5 days after March 11, 2003 (the effective date of AD 2003–04–06), accomplish the requirements of either paragraph (g) or (h) of this AD. After the effective date of this AD, only accomplishing the requirements of paragraph (g) of this AD is acceptable for compliance with this paragraph. Inspection To Determine Part Number (g) Perform a one-time general visual inspection of the modification plate for the Honeywell Primus II NV–850 Navigation Receiver Module (NRM); part number 7510134–811, –831, –901, or –931; which is part of the Honeywell Primus II RNZ–850( )/ –851( ) INU; to determine if Mod L has been installed. The modification plate is located on the bottom of the Honeywell Primus II RNZ–850( )/–851( ) INU, is labeled NV–850, and contains the part number and serial number for the Honeywell Primus II NV–850 NRM. If Mod L is installed, the letter L will be blacked out. Honeywell Alert Service Bulletin 7510100–34–A0035, dated July 11, 2003, is an acceptable source of service information for the inspection required by this paragraph. (1) If Mod L is installed, before further flight, do paragraph (h) or (j) of this AD. After the effective date of this AD, only accomplishment of paragraph (j) is acceptable for compliance with this paragraph. (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. VerDate Aug<31>2005 14:48 Oct 26, 2006 Jkt 211001 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 (g) of this AD, refer to Honeywell Technical Newsletter A23–3850–001, Revision 1, dated January 21, 2003. Aircraft Flight Manual (AFM) Revision (h) Revise the Limitations section of the 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 (i) As of March 11, 2003, no person may install a Honeywell Primus II NV–850 NRM on which Mod L has been installed, on the Honeywell Primus II RNZ–850( )/–851( ) INU of any aircraft, unless paragraph (h) or (k) of this AD is accomplished. As of the effective date of this AD, only accomplishment of paragraph (k) is acceptable for compliance with this paragraph. New Requirements of This AD Inspection To Determine Modification Level of NRM (j) For aircraft on which Mod L was found to be installed during the inspection required by paragraph (g) of this AD, or for aircraft on which paragraph (h) of this AD was accomplished: Within 24 months after the effective date of this AD, do an inspection of the modification plate on the Honeywell Primus II NV–850 NRM; part number 7510134–811, –831, –901, or –931; which is part of the Honeywell Primus II RNZ–850( )/ –851( ) INU; to determine if Mod L, N, P, R or T is installed. The modification plate located on the bottom of the Honeywell Primus II RNZ–850( )/–851( ) INU is labeled NV–850, and contains the part number and serial number for the Honeywell Primus II NV–850 NRM. If Mod L, N, P, R or T is installed, the corresponding letter on the modification plate will be blacked out. Honeywell Alert Service Bulletin 7510100– 34–A0035, dated July 11, 2003, is an acceptable source of service information for this inspection. If Mod T is installed, no further action is required by this paragraph. If Mod L, N, P, or R is installed, before further flight, do all applicable related investigative, corrective, and other specified actions, in accordance with the Accomplishment Instructions of Honeywell Alert Service Bulletin 7510100–34–A0035, PO 00000 Frm 00035 Fmt 4700 Sfmt 4700 62909 dated July 11, 2003; and Honeywell Service Bulletin 7510100–34–0037, dated July 8, 2004; to ensure that the NRM is at the Mod T configuration. Once the actions in this paragraph are completed, the AFM revision required by paragraph (h) of this AD may be removed from the AFM. Note 4: Honeywell Alert Service Bulletin 7510100–34–A0035, dated July 11, 2003, refers to Honeywell Alert Service Bulletin 7510100–34–A0034, dated February 28, 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. Honeywell Alert Service Bulletin 7510100–34–A0034 refers to Honeywell Alert Service Bulletin 7510134– 34–A0016, currently at Revision 001, dated March 4, 2003, as an additional source of service information for marking the modification plates of the NRM and INU. Note 5: Honeywell Service Bulletin 7510100–34–0037, dated July 8, 2004, refers to Honeywell Service Bulletin 7510134–34– 0018, dated July 8, 2004, as an additional source of service information for modifying the NRM to the Mod T configuration. (k) If the inspection specified in paragraph (j) of this AD is done within the compliance time specified in paragraph (f) of this AD, paragraph (g) of this AD does not need to be done. No Reporting Requirement (l) Where Honeywell Alert Service Bulletin 7510100–34–A0035, dated July 11, 2003 (or any of the related service information referenced therein), specifies to submit certain information to the manufacturer, this AD does not include that requirement. Alternative Methods of Compliance (AMOCs) (m)(1) The Manager, Los Angeles Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with 14 CFR 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Material Incorporated by Reference (n) You must use Honeywell Alert Service Bulletin 7510100–34–A0035, dated July 11, 2003; and Honeywell Service Bulletin 7510100–34–0037, dated July 8, 2004, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Go to https:// pubs.cas.honeywell.com or contact Honeywell International, Inc., Commercial Electronic Systems, 21111 North 19th Avenue, Phoenix, Arizona 85027–2708, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, E:\FR\FM\27OCR1.SGM 27OCR1 62910 Federal Register / Vol. 71, No. 208 / Friday, October 27, 2006 / Rules and Regulations 400 Seventh Street, SW., Room PL–401, Nassif Building, Washington, DC; on the Internet at https://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to https:// www.archives.gov/federal_register/code_of_ federal_regulations/ibr_locations.html. Issued in Renton, Washington, on October 13, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–17658 Filed 10–26–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24228; Directorate Identifier 2006–CE–22–AD; Amendment 39– 14805; AD 2006–22–08] RIN 2120–AA64 Airworthiness Directives; Air Tractor, Inc. Models AT–602, AT–802, and AT– 802A Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: SUMMARY: The FAA adopts a new airworthiness directive (AD) for all Air Tractor, Inc. Models AT–602, AT–802, and AT–802A airplanes. This AD requires you to repetitively inspect the engine mount for any cracks, repair or replace any cracked engine mount, and report any cracks found to the FAA. This AD results from reports of cracked engine mounts. We are issuing this AD to detect and correct cracks in the engine mount, which could result in failure of the engine mount. Such failure could lead to separation of the engine from the airplane. This AD becomes effective on December 1, 2006. As of December 1, 2006, the Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulation. ADDRESSES: To get the service information identified in this AD, contact Air Tractor, Inc., P.O. Box 485, Olney, Texas 76374; telephone: (940) 564–5616; facsimile: (940) 564–5612. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 001 or on the Internet at https:// dms.dot.gov. The docket number is FAA–2006–24228; Directorate Identifier 2006–CE–22–AD. FOR FURTHER INFORMATION CONTACT: Andrew McAnaul, Aerospace Engineer, ASW–150 (c/o MIDO–43), 10100 Reunion Place, Suite 650, San Antonio, Texas 78216; telephone: (210) 308– 3365; facsimile: (210) 308–3370. SUPPLEMENTARY INFORMATION: DATES: Discussion On April 26, 2006, we issued a proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to all Air Tractor, Inc. Models AT–602, AT– 802, and AT–802A airplanes. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on May 2, 2006 (71 FR 25793). The NPRM proposed to require you to repetitively inspect the engine mount for any cracks, repair or replace any cracked engine mount, and report any cracks found to the FAA. Comments We provided the public the opportunity to participate in developing this AD. The following presents the comment received on the proposal and FAA’s response to the comment: Labor cost Parts cost Total cost per airplane per inspection 1.5 work-hours × $80 per hour = $120 ................. Not Applicable ............... $120 rmajette on PROD1PC67 with RULES1 We have no way of determining the number of airplanes that may need replacement of the engine mount. We Parts cost Total cost per airplane per inspection 81 work-hours × $80 per hour = $6,480 ...................... $3,982 $10,462 14:48 Oct 26, 2006 Jkt 211001 Ronald G. Bush suggests that proper flight testing of a correctly instrumented engine mount and structure, combined with analysis of the data collected, may provide for a more efficient solution to the cracking problem than the repetitive inspections currently provide. He notes that the cost of each inspection is estimated at $120, and a properly substantiated terminating action may prove less costly over time. We partially agree that a properly executed flight test and analysis is a method to provide substantiating data that can be used to validate an alternate method for addressing the engine mount fatigue cracking. The FAA has not received any data at this time that proposes and substantiates a terminating action for the required inspections. If and when such information is received, we will consider mandating it through AD action. We are not changing the AD as a result of this comment. Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed except for minor editorial corrections. We have determined that these minor corrections: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Costs of Compliance We estimate that this AD affects 368 airplanes in the U.S. registry. We estimate the following costs to do each required inspection: Total cost on U.S. operators for initial inspection 368 × $120 = $44,160. estimate the following costs to do the replacement: Labor cost VerDate Aug<31>2005 Comment Issue: Flight Test and Analysis PO 00000 Frm 00036 Fmt 4700 Sfmt 4700 Total cost on U.S. operators for initial inspection 368 × $10,462 = $3,850,016. E:\FR\FM\27OCR1.SGM 27OCR1

Agencies

[Federal Register Volume 71, Number 208 (Friday, October 27, 2006)]
[Rules and Regulations]
[Pages 62907-62910]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-17658]



[[Page 62907]]

-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20080; Directorate Identifier 2003-NM-193-AD; 
Amendment 39-14802; AD 2006-22-05]
RIN 2120-AA64


Airworthiness Directives; Various Aircraft Equipped With 
Honeywell Primus II RNZ-850( )/-851( ) Integrated Navigation Units

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to various aircraft equipped with certain Honeywell 
Primus II RNZ-850( )/-851( ) integrated navigation units (INUs). That 
AD, as one alternative for compliance, provides for a one-time 
inspection to determine whether a certain modification has been 
installed on the Honeywell Primus II NV-850 navigation receiver module 
(NRM), which is part of the INU. In lieu of accomplishing this 
inspection, and for aircraft found to have an affected NRM, the 
existing AD provides for revising the aircraft flight manual to include 
new limitations for instrument landing system approaches. This new AD 
requires inspecting to determine whether certain modifications have 
been done on the NRM; and doing related investigative, corrective, and 
other specified actions, as applicable; as well as further 
modifications to address additional anomalies. This AD results from 
reports indicating that erroneous glideslope indications have occurred 
on certain aircraft equipped with the subject INUs. We are issuing this 
AD to ensure that the flightcrew has an accurate glideslope deviation 
indication. 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.

DATES: This AD becomes effective December 1, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of December 1, 
2006.

ADDRESSES: You may examine the AD docket on the Internet at https://dms.dot.gov or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street SW., Nassif Building, 
Room PL-401, Washington, DC.
    Go to https://pubs.cas.honeywell.com or contact Honeywell 
International, Inc., Commercial Electronic Systems, 21111 North 19th 
Avenue, Phoenix, Arizona 85027-2708, for service information identified 
in this AD.

FOR FURTHER INFORMATION CONTACT:
    J. Kirk Baker, Aerospace Engineer, Systems and Equipment Branch, 
ANM-130L, FAA, Los Angeles Aircraft Certification Office, 3960 
Paramount Boulevard, Lakewood, California 90712-4137; telephone (562) 
627-5345; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION:

Examining the Docket

    You may examine the airworthiness directive (AD) docket on the 
Internet at https://dms.dot.gov or in person at the Docket Management 
Facility office between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The Docket Management Facility office 
(telephone (800) 647-5227) is located on the plaza level of the Nassif 
Building at the street address stated in the ADDRESSES section.

Discussion

    The FAA issued a supplemental notice of proposed rulemaking (NPRM) 
to amend 14 CFR part 39 to include an AD that supersedes AD 2003-04-06, 
amendment 39-13054 (68 FR 8539, February 24, 2003). The existing AD 
applies to various aircraft equipped with certain Honeywell Primus II 
RNZ-850/-851 integrated navigation units (INUs). That supplemental NPRM 
was published in the Federal Register on May 18, 2006 (71 FR 28827). 
That supplemental NPRM proposed to continue to require inspecting to 
determine whether certain modifications have been done on the NRM; and 
doing related investigative, corrective, and other specified actions, 
as applicable; as well as further modifications to address additional 
anomalies.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments received from 
the single commenter.

Request To Clarify Reply to Comment to Original NPRM

    The commenter, Air Wisconsin, has requested an explanation of our 
reply to its comment to the original NPRM. The original comment 
requested clarification of the proposed requirements for inspecting to 
determine the modification level of the NRM and proposed that paragraph 
(k) of the original NPRM be revised to state that paragraph (j) of the 
AD need not be performed under certain conditions. The commenter 
asserts that our reply to that original comment was contradictory and 
confusing because we stated that we had made no change to paragraph (k) 
of the original NPRM when, in fact, paragraph (k) of the supplemental 
NPRM had been changed.
    We acknowledge the commenter's concern. As stated in our original 
reply, we determined that paragraph (j) of the AD is required 
regardless of compliance time or the findings of paragraph (f); this is 
because paragraph (j) requires inspecting for Mod N, P, R, or T, as 
well as Mod L. Therefore, we did not change paragraph (k) of the 
original NPRM as the commenter suggested. However, we determined that 
paragraph (k) was incorrect in that it stated that paragraph (f) did 
not need to be done if paragraph (j) was accomplished within the 
compliance time specified by paragraph (f). Paragraph (f) of the AD 
deals with compliance times and has no findings, while paragraph (g) of 
the AD requires an inspection and has findings. Therefore, it was our 
intent to revise paragraph (k) to read as it appears in the 
supplemental NPRM; that is, if paragraph (j) is accomplished within the 
compliance time specified by paragraph (f), paragraph (g) does not need 
to be done. We have made no further changes to paragraph (k) of the AD 
in this regard.

Explanation of Change To Applicability

    We have revised the applicability of the AD to identify model 
designations as published in the most recent type certificate data 
sheet for the affected models.

Clarification of INU References

    The applicability of the supplemental NPRM specifies that the AD 
applies to aircraft ``equipped with a Honeywell Primus II RNZ-850/-851 
INU having a part number identified in Table 1 of this AD.'' However, 
the Honeywell service bulletins identified in the following table 
variously refer to ``-850/-851,'' ``-850/A/B/C,'' ``-851/A/B/C,'' and 
``-850(X)/-851(X)'' INUs, indicating that the RNZ-850/-851 part number 
might or might not contain a suffix letter. Although the service 
bulletins identified in the following table make it clear that the INU 
part numbers, as identified in Table 1 of the AD, are the primary 
identifiers of all affected INUs, we have determined that these various 
suffix references could cause confusion. Therefore, to address all 
references to suffix letters in the service bulletins, we

[[Page 62908]]

have revised the AD to read ``-850( )/-851( )'' where applicable.

                      Honeywell Service Information
------------------------------------------------------------------------
                                  Revision
          Honeywell                level                 Date
------------------------------------------------------------------------
Alert Service Bulletin         Original.....  February 28, 2003.
 7510100-34-A0034.
Alert Service Bulletin         Original.....  July 11, 2003.
 7510100-34-A0035.
Alert Service Bulletin         001..........  March 4, 2003.
 7510134-34-A0016.
Service Bulletin 7510134-34-   Original.....  July 8, 2004.
 0018.
Service Bulletin 7510100-34-   Original.....  July 8, 2004.
 0037.
------------------------------------------------------------------------

Conclusion

    We have carefully reviewed the available data, including the 
comments received, and determined that air safety and the public 
interest require adopting the AD with the changes described previously. 
We have determined that these changes will neither increase the 
economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    For the purposes of this AD, we estimate that there are 3,063 
aircraft worldwide that may be equipped with a part that is subject to 
this AD, including about 1,500 aircraft of U.S. registry.
    The inspection to determine whether Mod L has been done, which is 
currently required by AD 2003-04-06 and retained in this AD, will take 
about 1 work hour per aircraft, at an average labor rate of $80 per 
work hour. Based on these figures, the estimated cost of the currently 
required actions is $80 per aircraft.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing amendment 39-13054 (68 FR 
8539, February 24, 2003) and adding the following new airworthiness 
directive (AD):

2006-22-05 Various Aircraft: Amendment 39-14802. Docket No. FAA-
2005-20080; Directorate Identifier 2003-NM-193-AD.

Effective Date

    (a) This AD becomes effective December 1, 2006.

Affected ADs

    (b) This AD supersedes AD 2003-04-06.

Applicability

    (c) This AD applies to aircraft, certificated in any category, 
equipped with a Honeywell Primus II RNZ-850( )/-851( ) integrated 
navigation unit (INU) 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 Model BD-700-
1A10 series airplanes; Model Bombardier CL-215-6B11 (CL-415 variant) 
series airplanes; Cessna Model 560, 560XL, and 650 airplanes; 
Dassault Model Mystere-Falcon 50 series airplanes; AvCraft Dornier 
Model 328-100 and -300 series airplanes; Empresa Brasileira de 
Aeronautica S.A. (EMBRAER) Model EMB-135 airplanes and Model EMB-
145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP 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.--INU Part Numbers
------------------------------------------------------------------------
                                Part Nos.
-------------------------------------------------------------------------
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( 
) INUs 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 (m) of this AD. The request should include an assessment 
of the effect of the

[[Page 62909]]

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.

Unsafe Condition

    (d) This AD results from reports indicating that erroneous 
glideslope indications have occurred on certain aircraft equipped 
with the subject INUs. We are issuing this AD to ensure that the 
flightcrew has an accurate glideslope deviation indication. 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.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Requirements of AD 2003-04-06

Compliance Time For Action

    (f) Within 5 days after March 11, 2003 (the effective date of AD 
2003-04-06), accomplish the requirements of either paragraph (g) or 
(h) of this AD. After the effective date of this AD, only 
accomplishing the requirements of paragraph (g) of this AD is 
acceptable for compliance with this paragraph.

Inspection To Determine Part Number

    (g) Perform a one-time general visual inspection of the 
modification plate for the Honeywell Primus II NV-850 Navigation 
Receiver Module (NRM); part number 7510134-811, -831, -901, or -931; 
which is part of the Honeywell Primus II RNZ-850( )/-851( ) INU; to 
determine if Mod L has been installed. The modification plate is 
located on the bottom of the Honeywell Primus II RNZ-850( )/-851( ) 
INU, is labeled NV-850, and contains the part number and serial 
number for the Honeywell Primus II NV-850 NRM. If Mod L is 
installed, the letter L will be blacked out. Honeywell Alert Service 
Bulletin 7510100-34-A0035, dated July 11, 2003, is an acceptable 
source of service information for the inspection required by this 
paragraph.
    (1) If Mod L is installed, before further flight, do paragraph 
(h) or (j) of this AD. After the effective date of this AD, only 
accomplishment of paragraph (j) is acceptable for compliance with 
this paragraph.
    (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 (g) of this AD, refer to Honeywell Technical Newsletter 
A23-3850-001, Revision 1, dated January 21, 2003.

Aircraft Flight Manual (AFM) Revision

    (h) Revise the Limitations section of the 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

    (i) As of March 11, 2003, no person may install a Honeywell 
Primus II NV-850 NRM on which Mod L has been installed, on the 
Honeywell Primus II RNZ-850( )/-851( ) INU of any aircraft, unless 
paragraph (h) or (k) of this AD is accomplished. As of the effective 
date of this AD, only accomplishment of paragraph (k) is acceptable 
for compliance with this paragraph.

New Requirements of This AD

Inspection To Determine Modification Level of NRM

    (j) For aircraft on which Mod L was found to be installed during 
the inspection required by paragraph (g) of this AD, or for aircraft 
on which paragraph (h) of this AD was accomplished: Within 24 months 
after the effective date of this AD, do an inspection of the 
modification plate on the Honeywell Primus II NV-850 NRM; part 
number 7510134-811, -831, -901, or -931; which is part of the 
Honeywell Primus II RNZ-850( )/-851( ) INU; to determine if Mod L, 
N, P, R or T is installed. The modification plate located on the 
bottom of the Honeywell Primus II RNZ-850( )/-851( ) INU is labeled 
NV-850, and contains the part number and serial number for the 
Honeywell Primus II NV-850 NRM. If Mod L, N, P, R or T is installed, 
the corresponding letter on the modification plate will be blacked 
out. Honeywell Alert Service Bulletin 7510100-34-A0035, dated July 
11, 2003, is an acceptable source of service information for this 
inspection. If Mod T is installed, no further action is required by 
this paragraph. If Mod L, N, P, or R is installed, before further 
flight, do all applicable related investigative, corrective, and 
other specified actions, in accordance with the Accomplishment 
Instructions of Honeywell Alert Service Bulletin 7510100-34-A0035, 
dated July 11, 2003; and Honeywell Service Bulletin 7510100-34-0037, 
dated July 8, 2004; to ensure that the NRM is at the Mod T 
configuration. Once the actions in this paragraph are completed, the 
AFM revision required by paragraph (h) of this AD may be removed 
from the AFM.

    Note 4: Honeywell Alert Service Bulletin 7510100-34-A0035, dated 
July 11, 2003, refers to Honeywell Alert Service Bulletin 7510100-
34-A0034, dated February 28, 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. Honeywell Alert Service 
Bulletin 7510100-34-A0034 refers to Honeywell Alert Service Bulletin 
7510134-34-A0016, currently at Revision 001, dated March 4, 2003, as 
an additional source of service information for marking the 
modification plates of the NRM and INU.


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

    (k) If the inspection specified in paragraph (j) of this AD is 
done within the compliance time specified in paragraph (f) of this 
AD, paragraph (g) of this AD does not need to be done.

No Reporting Requirement

    (l) Where Honeywell Alert Service Bulletin 7510100-34-A0035, 
dated July 11, 2003 (or any of the related service information 
referenced therein), specifies to submit certain information to the 
manufacturer, this AD does not include that requirement.

Alternative Methods of Compliance (AMOCs)

    (m)(1) The Manager, Los Angeles Aircraft Certification Office 
(ACO), FAA, has the authority to approve AMOCs for this AD, if 
requested in accordance with the procedures found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with 14 CFR 
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Material Incorporated by Reference

    (n) You must use Honeywell Alert Service Bulletin 7510100-34-
A0035, dated July 11, 2003; and Honeywell Service Bulletin 7510100-
34-0037, dated July 8, 2004, to perform the actions that are 
required by this AD, unless the AD specifies otherwise. The Director 
of the Federal Register approved the incorporation by reference of 
these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Go to https://pubs.cas.honeywell.com or contact Honeywell 
International, Inc., Commercial Electronic Systems, 21111 North 19th 
Avenue, Phoenix, Arizona 85027-2708, for a copy of this service 
information. You may review copies at the Docket Management 
Facility, U.S. Department of Transportation,

[[Page 62910]]

400 Seventh Street, SW., Room PL-401, Nassif Building, Washington, 
DC; on the Internet at https://dms.dot.gov; or at the National 
Archives and Records Administration (NARA). For information on the 
availability of this material at the NARA, call (202) 741-6030, or 
go to https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on October 13, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-17658 Filed 10-26-06; 8:45 am]
BILLING CODE 4910-13-P
This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.