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

[Federal Register Volume 68, Number 36 (Monday, February 24, 2003)]
[Rules and Regulations]
[Pages 8539-8541]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-4238]



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Federal Register / Vol. 68, No. 36 / Monday, February 24, 2003 / 
Rules and Regulations

[[Page 8539]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-41-AD; Amendment 39-13054; AD 2003-04-06]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to various aircraft equipped with a certain Honeywell 
Primus II RNZ-850/-851 Integrated Navigation Unit. As one alternative 
for compliance, this action provides for a one-time inspection to 
determine whether a certain modification has been installed on the 
Honeywell Primus II NV850 Navigation Receiver Module, which is part of 
the Integrated Navigation Unit. In lieu of accomplishing this 
inspection, and for aircraft found to have an affected navigation 
receiver module, this action provides for revising the aircraft flight 
manual to include new limitations for instrument landing system (ILS) 
approaches. This action is necessary 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. This action is intended to address the identified unsafe 
condition.

DATES: Effective March 11, 2003.
    Comments for inclusion in the Rules Docket must be received on or 
before April 25, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2003-NM-41-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2003-NM-41-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 for Windows or 
ASCII text.
    The information referenced in this AD may be examined at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington; or at the FAA, Los Angeles Aircraft Certification Office, 
3960 Paramount Boulevard, Lakewood, California.

FOR FURTHER INFORMATION CONTACT: George Mabuni, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130L, FAA, Los Angeles Aircraft 
Certification Office, 3960 Paramount Boulevard, Lakewood, California 
90712-4137; telephone (562) 627-5341; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: The FAA has received reports indicating that 
erroneous glideslope indications have occurred on certain Empresa 
Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-145 series 
airplanes. In these incidents, the glideslope deviation indicator 
unexpectedly changed from a centered 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 Navigation Receiver Modules that are 
part of the Honeywell Primus II RNZ-850/-851 Integrated Navigation 
Units installed on the affected airplanes. 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.
    Affected Honeywell Primus II RNZ-850/-851 Integrated Navigation 
Units are installed on numerous aircraft models. Affected aircraft 
models include, but are 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; EMBRAER Model EMB-135 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. All aircraft models 
equipped with affected integrated navigation units may be subject to 
the same unsafe condition revealed on the EMBRAER Model EMB-145 series 
airplanes.

Explanation of the Requirements of the Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design, this AD is 
being issued 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. As one alternative 
for compliance, this AD provides for a one-time inspection to determine 
whether an affected navigation receiver module is installed. In lieu of 
this inspection, and for aircraft with an affected navigation receiver 
module, the AD also requires revising the Limitations section of the 
aircraft flight manual to include new limitations for ILS approaches.

Relevant Technical Discussions

    During the development of this AD, the FAA received information 
demonstrating that the planned AD would present significant operational 
difficulties for affected operators. First, we learned that 
accomplishing the inspection specified in paragraph (b) of

[[Page 8540]]

this AD within the specified compliance time could result in service 
delays and out-of-service time for affected aircraft. We also received 
information that the revision to the Limitations section that we were 
considering was too restrictive for certain airplanes and would have an 
adverse impact on operations. Further, because a majority of the fleet 
of affected aircraft is expected to be equipped with an affected 
navigation receiver module, we found that the adverse impact of this AD 
would be widespread.
    In light of this information, we held further discussions with the 
manufacturer of the subject parts and representatives of industry. Data 
presented during these discussions led us to reconsider the degree of 
urgency of the identified unsafe condition and the requirements of this 
AD.

Interim Action

    This is considered to be interim action. The manufacturer has 
advised that it currently is developing a modification that will 
address the unsafe condition addressed by this AD. Once this 
modification is developed, approved, and available, the FAA may 
consider additional rulemaking.

Determination of Rule's Effective Date

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this rule by 
submitting such written data, views, or arguments as they may desire. 
Communications shall identify the Rules Docket number and be submitted 
in triplicate to the address specified under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Submit comments using the following format:
    [sbull] Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
    [sbull] For each issue, state what specific change to the AD is 
being requested.
    [sbull] Include justification (e.g., reasons or data) for each 
request.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2003-NM-41-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    The regulations adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, may be obtained from the Rules Docket at the 
location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    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]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

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.

[[Page 8541]]

    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, Revision 1, 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.

    Issued in Renton, Washington, on February 14, 2003.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-4238 Filed 2-21-03; 8:45 am]
BILLING CODE 4910-13-P

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