[Federal Register: January 19, 2005 (Volume 70, Number 12)]
[Proposed Rules]
[Page 2982-2985]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr19ja05-19]
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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://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
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Corresponding requirement
Requirement in AD 2003-04-06 in this proposed AD
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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
[[Page 2984]]
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
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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 (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]
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