[Federal Register Volume 70, Number 12 (Wednesday, January 19, 2005)]
[Proposed Rules]
[Pages 2982-2985]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-992]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20080; Directorate Identifier 2003-NM-193-AD]
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: Notice of proposed rulemaking (NPRM).

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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.

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:

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

[[Page 2983]]

consider 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://
http://dms.dot.gov">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://
http://dms.dot.gov">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
------------------------------------------------------------------------
                                             Corresponding  requirement
       Requirement in AD 2003-04-06             in this  proposed AD
------------------------------------------------------------------------
paragraph (a).............................  paragraph (f).
paragraph (b).............................  paragraph (g).
paragraph (c).............................  paragraph (h).
paragraph (d).............................  paragraph (i).
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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

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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 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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. 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):

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
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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):

[[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.

    Issued in Renton, Washington, on January 7, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-992 Filed 1-18-05; 8:45 am]
BILLING CODE 4910-13-P