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Proposed Rule

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

Document Details

Information about this document as published in the Federal Register.

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Start Preamble

AGENCY:

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

ACTION:

Notice of proposed rulemaking (NPRM).

SUMMARY:

The FAA proposes to supersede an existing airworthiness directive (AD) that applies to various aircraft equipped with a certain Honeywell Primus II RNZ-850/-851 Integrated Navigation Unit (INU). The existing AD requires inspecting to determine whether Mod L has been done on the Honeywell Primus II NV850 Navigation Receiver Module (NRM), which is part of the INU. In lieu of this inspection, or for aircraft with an NRM having Mod L, the existing AD requires revising the aircraft flight manual to include new limitations for instrument landing system approaches. For aircraft equipped with an NRM having Mod L or aircraft not inspected previously, this proposed AD would require inspecting to determine whether certain other modifications have been done on the NRM; and doing related investigative, corrective, and other specified actions, as applicable. This proposed AD is prompted by reports of erroneous glide slope indications on certain aircraft equipped with subject INUs. We are proposing 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:

We must receive comments on this proposed AD by March 7, 2005.

ADDRESSES:

Use one of the following addresses to submit comments on this proposed AD.

  • DOT Docket Web site: Go to http//dms.dot.gov and follow the instructions for sending your comments electronically.
  • Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically.
  • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590.
  • Fax: (202) 493-2251.
  • Hand Delivery: Room PL-401 on the plaza level of the Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this proposed AD, contact Honeywell Aerospace Electronic Systems, CES-Phoenix, P.O. Box 2111, Phoenix, Arizona 85036-1111.

You can examine the contents of this AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL-401, on the plaza level of the Nassif Building, Washington, DC.

Start Further Info

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.

End Further Info End Preamble Start Supplemental Information

SUPPLEMENTARY INFORMATION:

Comments Invited

We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed under ADDRESSES. Include “Docket No. FAA-2005-20080; Directorate Identifier 2003-NM-193-AD” at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will Start Printed Page 2983consider all comments received by the closing date and may amend the proposed AD in light of those comments.

We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of our docket Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You can review the DOT's complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477-78), or you can visit http://dms.dot.gov.

Examining the Docket

You can examine the AD docket on the Internet at http://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 DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the DMS receives them.

Discussion

On February 14, 2003, we issued AD 2003-04-06, amendment 39-13054 (68 FR 8539, February 24, 2003), for various aircraft equipped with a certain Honeywell Primus II RNZ-850/-851 Integrated Navigation Unit (INU). As one alternative for compliance, that AD provides for a one-time inspection to determine whether a certain modification has been installed on the Honeywell Primus II NV850 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, that AD provides for revising the aircraft flight manual to include new limitations for instrument landing system approaches. That AD was prompted by reports indicating that erroneous glideslope indications have occurred on certain Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-145 series airplanes. Affected Honeywell Primus II RNZ-850/-851 INUs are installed on numerous aircraft models. We issued that 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.

The preamble to AD 2003-04-06 specified that we considered the requirements “interim action” and that the manufacturer was developing a modification to address the unsafe condition. That AD explained that we may consider further rulemaking if a modification is developed, approved, and available. The manufacturer now has developed such a modification, and we have determined that further rulemaking is indeed necessary; this proposed AD follows from that determination.

Relevant Service Information

We have reviewed Honeywell Service Bulletin 7510100-34-A0035, dated July 11, 2003, which describes procedures for inspecting the NRM to determine whether Mod L has been done. If Mod L has not been done, the service bulletin specifies re-identifying the NRM with a new part number. If Mod L has been done, the service bulletin specifies inspecting to determine if Mod N, P, or R has also been done. (Mod N, P, and R test the NRM for discrepant signals.) If any of those mods has been done, the specified actions are replacing the existing modification plates on the NRM and INU with new plates bearing new part numbers. If Mod L has been done, but neither Mod N, P, nor R has been done, the service bulletin specifies doing further investigative actions and corrective actions in accordance with Honeywell Service Bulletin 7510100-34-A0034, then replacing the existing modification plates on the NRM and INU with new plates bearing new part numbers.

Honeywell Service Bulletin 7510100-34-A0034, dated February 28, 2003, describes procedures for inspecting to determine the NRM part number and marking the modification plates of the NRM and INU accordingly. This service bulletin also describes procedures for a related investigative action if neither Mod N nor P is marked, which consists of testing the INU for discrepant signals. If any discrepant signal is detected, corrective action consists of replacing the unit with a new or modified INU. Honeywell Service Bulletin 7510100-34-A0034 refers to Honeywell Service Bulletin 7510134-34-A0016, currently at Revision 001, dated March 4, 2003, as an additional source of service information for re-identifying the INU.

Accomplishing the actions specified in this service information is intended to adequately address the unsafe condition.

FAA's Determination and Requirements of the Proposed AD

We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other products of this same type design. This proposed AD would supersede AD 2003-04-06. This proposed AD would retain the requirements of the existing AD. This proposed AD would also require accomplishing the actions specified in the service information described previously, except as discussed under “Differences Between the Proposed AD and Service Information.”

Differences Between the Proposed AD and Service Information

The service information specifies reporting certain information and returning parts to the manufacturer. However, this proposed AD would not require those actions.

Change to Existing AD

This proposed AD would retain all requirements of AD 2003-04-06. Since AD 2003-04-06 was issued, the AD format has been revised, and certain paragraphs have been rearranged. As a result, the corresponding paragraph identifiers have changed in this proposed AD, as listed in the following table:

Revised Paragraph Identifiers

Requirement in AD 2003-04-06Corresponding requirement in this proposed AD
paragraph (a)paragraph (f).
paragraph (b)paragraph (g).
paragraph (c)paragraph (h).
paragraph (d)paragraph (i).

Costs of Compliance

For the purposes of this proposed AD, we estimate that there are about 3,063 aircraft worldwide that may be equipped with a part that is subject to this proposed 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 proposed AD, takes about 1 work hour per aircraft, at an average labor rate of $65 per work hour. Based on these figures, the estimated cost of the currently required actions is $65 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 Start Printed Page 2984the 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 the proposed regulation:

1. Is not a “significant regulatory action” under Executive Order 12866;

2. Is not a “significant rule” under the 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 proposed AD. See the ADDRESSES section for a location to examine the regulatory evaluation.

Start List of Subjects

List of Subjects in 14 CFR Part 39

End List of Subjects

The Proposed Amendment

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

Start Part

PART 39—AIRWORTHINESS DIRECTIVES

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

Start Authority

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

End Authority
[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):

Various Aircraft: Docket No. FAA-2005-20080; Directorate Identifier 2003-NM-193-AD.

Comments Due Date

(a) The Federal Aviation Administration must receive comments on this airworthiness directive (AD) action by March 7, 2005.

Affected ADs

(b) This AD supersedes AD 2003-04-06, amendment 39-13054 (68 FR 8539, February 24, 2003).

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 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.—INU 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 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 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 was prompted by 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, amendment 39-13054), 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 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 Revision

(h) 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): Start Printed Page 2985

“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 12 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, or R 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, or R is installed, the corresponding letter on the modification plate will be blacked out. Honeywell Service Bulletin 7510100-34-A0035, dated July 11, 2003, is an acceptable source of service information for this inspection. Then, before further flight, do all applicable related investigative, corrective, and other specified actions, in accordance with the Accomplishment Instructions of Honeywell Service Bulletin 7510100-34-A0035, dated July 11, 2003. 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 Service Bulletin 7510100-34-A0035, dated July 11, 2003, refers to Honeywell 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 Service Bulletin 7510100-34-A0034 refers to Honeywell 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.

(k) If the inspection to determine whether Mod L is installed, as required by paragraph (j) of this AD, is done within the compliance time specified in paragraph (f) of this AD, paragraph (f) of this AD does not need to be done.

No Reporting Requirement

(l) Where Honeywell Service Bulletin 7510100-34-A0035 (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) 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.

Start Signature

Issued in Renton, Washington, on January 7, 2005.

Ali Bahrami,

Manager, Transport Airplane Directorate, Aircraft Certification Service.

End Signature End Part End Supplemental Information

[FR Doc. 05-992 Filed 1-18-05; 8:45 am]

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