[Federal Register Volume 73, Number 97 (Monday, May 19, 2008)]
[Proposed Rules]
[Pages 28751-28754]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E8-11104]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0556; Directorate Identifier 2007-NM-028-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 certain 
Honeywell Primus II RNZ-850( )/-851( ) integrated navigation units 
(INUs). The existing 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, that AD provides for revising the aircraft flight manual 
to include new limitations for instrument landing system approaches. 
That AD also requires an inspection to determine whether certain other 
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 
proposed AD would extend the compliance time for a certain inspection 
and associated actions. This proposed AD would also revise the 
applicability to include additional affected INUs. This proposed AD 
results from reports indicating that erroneous localizer and glideslope 
indications have occurred on certain aircraft equipped with the subject 
INUs. We are proposing this AD to ensure that the flight crew has 
accurate localizer and glideslope deviation indications. An erroneous 
localizer or glideslope deviation indication could lead to the aircraft 
making an approach off the localizer, which could result in impact with 
an obstacle or terrain.

DATES: We must receive comments on this proposed AD by July 3, 2008.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
https://pubs.cas.honeywell.com or contact Honeywell International, 
Inc., Commercial Electronic Systems, 21111 North 19th Avenue, Phoenix, 
Arizona 85027-2708.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (telephone 800-647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

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 send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-0556; 
Directorate Identifier 2007-NM-028-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On October 13, 2006, we issued AD 2006-22-05, amendment 39-14802 
(71 FR 62907, October 27, 2006), for 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, that AD 
provides for revising the aircraft flight manual to include new 
limitations for instrument landing system approaches. That AD also 
requires an inspection to determine whether certain other 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. That AD resulted from 
reports indicating that erroneous glideslope indications have occurred 
on certain aircraft equipped with the subject INUs. 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.

Actions Since Existing AD Was Issued

    Since we issued AD 2006-22-05, we have become aware of the need to 
change three aspects of the existing AD:
    1. Additional INU part numbers need to be added to the 
applicability.
    2. Paragraph (j) of the existing AD requires related investigative, 
corrective, and other specified actions for certain NRMs before further 
flight. Our intention was to allow the full compliance time for both 
the inspection for the discrepant NRMs and the other associated actions 
for those NRMs.

[[Page 28752]]

    3. We have determined that the existing AD's compliance time for 
the inspection and other associated actions (paragraph (j) in the NPRM) 
may be extended to 30 months and still provide an adequate level of 
safety for the fleet.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to develop on other products of the 
same type design. For this reason, we are proposing this AD, which 
would supersede AD 2006-22-05 and retain its requirements, with revised 
compliance times for a certain inspection and other associated actions. 
This proposed AD would also revise the applicability to include 
additional affected INUs.

Additional Changes to Existing AD

    Where paragraph (i) of the existing AD incorrectly refers to 
paragraph (k), the proper reference should be to paragraph (j). We have 
revised this proposed AD accordingly.
    We also clarified the unsafe condition by also referring to the 
localizer (in addition to the glideslope).

Costs of Compliance

    There are about 3,063 aircraft of the affected design in the 
worldwide fleet. The following table provides the estimated costs for 
U.S. operators to comply with this proposed AD. The manufacturer states 
that it will supply required parts to existing customers at no cost.

                                                                     Estimated Costs
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                                                       Average
               Action                  Work hours    labor rate       Parts       Cost per        Number of U.S.-                  Fleet cost
                                                      per hour                    aircraft      registered aircraft
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Inspection for NRM modification                  1           $80            $0           $80  Up to 1,500............  Up to $120,000.
 level.
AFM revision........................             1            80             0            80  Up to 1,500............  Up to $120,000.
Modification (to Mod T                           1            80             0            80  Up to 1,500............  Up to $120,000.
 configuration).
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    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the proposed actions 
specified in this NPRM, and that no operator would accomplish those 
actions in the future if this AD were not adopted. We have been 
advised, however, that the actions have already been done on some 
affected airplanes. Therefore, the future economic cost impact of this 
rule on U.S. operators is expected to be less than the cost impact 
figures indicated above.

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 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 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, 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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-14802 (71 FR 62907, October 27, 2006) and adding 
the following new airworthiness directive (AD):

Various Aircraft: Docket No. FAA-2008-0556; Directorate Identifier 
2007-NM-028-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by July 3, 
2008.

Affected ADs

    (b) This AD supersedes AD 2006-22-05.

Applicability

    (c) This AD applies to various aircraft, certificated in any 
category, equipped with any Honeywell Primus II RNZ-850( )/-851( ) 
integrated navigation unit (INU) identified in a service bulletin 
identified in Table 1 of this AD. The aircraft include but are not 
limited to BAE Systems (Operations) Limited (Jetstream) Model 4101 
airplanes; Bombardier Model BD-700-1A10 series airplanes; Bombardier 
Model 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

[[Page 28753]]

airplanes; Raytheon Model Hawker 800XP and Hawker 1000 airplanes; 
and Sikorsky Model S-76A, S-76B, and S-76C aircraft.

                                       Table 1.--INUs Affected by This AD
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      INUs listed in Honeywell--                     Revision--                            Dated--
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(1) Alert Service Bulletin 7510134-34-  001................................  March 4, 2003.
 A0016.
(2) Service Bulletin 7510134-34-0018..  Original...........................  July 8, 2004.
(3) Alert Service Bulletin 7510100-34-  Original...........................  February 28, 2003.
 A0034.
(4) Alert Service Bulletin 7510100-34-  Original...........................  July 11, 2003.
 A0035.
(5) Service Bulletin 7510100-34-0037..  Original...........................  July 8, 2004.
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    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 (o) 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 results from reports indicating that erroneous 
localizer and glideslope indications have occurred on certain 
aircraft equipped with the subject INUs. We are issuing this AD to 
ensure that the flight crew has accurate localizer and glideslope 
deviation indications. An erroneous localizer or glideslope 
deviation indication could lead to the aircraft making an approach 
off the localizer, 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.

Restatement of Certain Requirements of AD 2006-22-05

Compliance Time for Action

    (f) For any INU identified in Table 2 of this AD: Within 5 days 
after March 11, 2003 (the effective date of AD 2003-04-06, which was 
superseded by AD 2006-22-05), accomplish the requirements of either 
paragraph (g) or (h) of this AD. After December 1, 2006 (the 
effective date of AD 2006-22-05), only accomplishing the 
requirements of paragraph (g) of this AD is acceptable for 
compliance with this paragraph.

               Table 2.--INUs Identified in AD 2006-22-05
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P/N 7510100-811 through 7510100-814 inclusive.
P/N 7510100-831 through 7510100-834 inclusive.
P/N 7510100-901 through 7510100-904 inclusive.
P/N 7510100-911 through 7510100-914 inclusive.
P/N 7510100-921 through 7510100-924 inclusive.
P/N 7510100-931 through 7510100-934 inclusive.
------------------------------------------------------------------------

Inspection to Determine Part Number

    (g) For any INU identified in Table 2 of this AD: 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 December 1, 2006, 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.''

Aircraft Flight Manual (AFM) Revision

    (h) For aircraft having an INU identified in Table 2 of this AD: 
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) For aircraft having an INU identified in Table 2 of this AD: 
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 (j) of this AD is accomplished. As of December 1, 2006, only 
accomplishment of paragraph (j) is acceptable for compliance with 
this paragraph.

Inspection to Determine Modification Level of NRM

    (j) For any INU identified in Table 2 of this AD 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 30 months after December 1, 2006, 
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, within 30 months after December 1, 2006, 
do all applicable related investigative, corrective, and other 
specified actions, in accordance with the Accomplishment 
Instructions of Honeywell

[[Page 28754]]

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.
    (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.

New Requirements of This AD

Inspection to Determine Mod Level

    (l) For any INU that is not identified in Table 2 of this AD: 
Within 30 months after the effective date of this AD, 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 whether 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.
    (1) If Mod T is installed: No further action is required by this 
paragraph.
    (2) If Mod L, N, P, or R is installed: Within 30 months after 
the effective date of this AD, 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.

    Note 3: For more information on the inspection specified in 
paragraphs (g), (j), and (l) of this AD, refer to Honeywell 
Technical Newsletter A23-3850-001, Revision 1, dated January 21, 
2003.

Parts Installation

    (m) For aircraft that have an INU that is not identified in 
Table 2 of this AD: As of the effective date of this AD, 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 (l) is accomplished.

No Report

    (n) 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)

    (o)(1) The Manager, Los Angeles Aircraft Certification Office, 
FAA, has the authority to approve AMOCs for this AD, if requested in 
accordance with the procedures found in 14 CFR 39.19.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any aircraft to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.

    Issued in Renton, Washington, on May 10, 2008.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E8-11104 Filed 5-16-08; 8:45 am]
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