Airworthiness Directives; Various Aircraft Equipped With Honeywell Primus II RNZ-850/-851 Integrated Navigation Units, 2982-2985 [05-992]
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Federal Register / Vol. 70, No. 12 / Wednesday, January 19, 2005 / Proposed Rules
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:
the compliance times specified, unless the
actions have already been done.
Modification
(f) Within 6 months after the effective date
of this AD: Modify the OPS of the ADIRU by
doing the applicable actions specified in the
Accomplishment Instructions of Boeing
Service Bulletin 777–34A0082, Revision 1,
dated December 19, 2002.
Alternative Methods of Compliance
(AMOCs)
(g) The Manager, Seattle 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.
Issued in Renton, Washington, on January
7, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–991 Filed 1–18–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
PART 39—AIRWORTHINESS
DIRECTIVES
Federal Aviation Administration
1. The authority citation for part 39
continues to read as follows:
14 CFR Part 39
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
RIN 2120–AA64
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
Boeing: Docket No. FAA–2005–20081;
Directorate Identifier 2004–NM–132–AD.
Comments Due Date
(a) The Federal Aviation Administration
(FAA) must receive comments on this AD
action by March 7, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 777–
200 and –300 series airplanes, certificated in
any category; as listed in Boeing Service
Bulletin 777–34A0082, Revision 1, dated
December 19, 2002.
Unsafe Condition
(d) This AD was prompted by a report of
the display of erroneous heading information
to the pilot due to a defect in the operational
program software (OPS) of the air data
inertial reference unit (ADIRU). The Federal
Aviation Administration is issuing this AD to
prevent the display of erroneous heading
information to the pilot, which could result
in loss of the main sources of attitude data,
consequent high pilot workload, and
subsequent deviation from the intended
flight path.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
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15:09 Jan 18, 2005
[Docket No. FAA–2005–20080; Directorate
Identifier 2003–NM–193–AD]
Jkt 205001
Airworthiness Directives; Various
Aircraft Equipped With Honeywell
Primus II RNZ–850/–851 Integrated
Navigation Units
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
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,
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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 https://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 https://
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
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Federal Register / Vol. 70, No. 12 / Wednesday, January 19, 2005 / Proposed Rules
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 https://
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 https://
dms.dot.gov.
Examining the Docket
You can examine the AD docket on
the Internet at https://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
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Jkt 205001
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.
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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
2003–04–06
paragraph
paragraph
paragraph
paragraph
(a)
(b)
(c)
(d)
.............
.............
.............
.............
Corresponding
requirement in this
proposed AD
paragraph
paragraph
paragraph
paragraph
(f).
(g).
(h).
(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
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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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing amendment 39–13054 (68 FR
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15:09 Jan 18, 2005
Jkt 205001
8539, February 24, 2003) and adding the
following new airworthiness directive
(AD):
making an approach off the glideslope, which
could result in impact with an obstacle or
terrain.
Various Aircraft: Docket No. FAA–2005–
20080; Directorate Identifier 2003–NM–
193–AD.
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.
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 MystereFalcon 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
7510100–831
7510100–901
7510100–911
7510100–921
7510100–931
through
through
through
through
through
through
7510100–814
7510100–834
7510100–904
7510100–914
7510100–924
7510100–934
inclusive
inclusive
inclusive
inclusive
inclusive
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
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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):
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‘‘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–
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15:09 Jan 18, 2005
Jkt 205001
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.
2985
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
crewmembers are informed of the risks
associated with forcibly opening
passenger/crew, emergency exit, and
cargo doors before an airplane is fully
depressurized, which will prevent
injury to crewmembers, and subsequent
damage to the airplane caused by the
rapid opening of the door.
DATES: We must receive comments on
this proposed AD by February 18, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://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.
• By 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 Airbus, 1
Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France.
You can examine the contents of this
AD docket on the Internet at https://
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.
This docket number is FAA–2005–
20079; the directorate identifier for this
docket is 2004–NM–147–AD.
FOR FURTHER INFORMATION CONTACT: Tim
Backman, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
98055–4056; telephone (425) 227–2797;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Airbus models, as specified
above. This proposed AD would require
installing safety signs on all passenger/
crew doors, emergency exit doors, and
cargo compartment doors. This
proposed AD is prompted by a report of
injuries occurring on in-service
airplanes when crewmembers forcibly
initiated opening of passenger/crew
doors against residual pressure causing
the doors to rapidly open. We are
proposing this AD to ensure that
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–
2005–20079; Directorate Identifier
2004–NM–147–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
consider all comments submitted by the
closing date and may amend the
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
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20079; Directorate
Identifier 2004–NM–147–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A300 B2 and B4 Series Airplanes;
Model A300 B4–600, B4–600R, and F4–
600R Series Airplanes, and Model C4–
605R Variant F Airplanes (Collectively
Called A300–600); and Model A310
Series Airplanes
AGENCY:
PO 00000
Frm 00023
Fmt 4702
Sfmt 4702
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19JAP1
]]>Agencies
[Federal Register Volume 70, Number 12 (Wednesday, January 19, 2005)]
[Proposed Rules]
[Pages 2982-2985]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-992]
-----------------------------------------------------------------------
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).
-----------------------------------------------------------------------
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 https://
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
https://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 https://
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 https://dms.dot.gov.
Examining the Docket
You can examine the AD docket on the Internet at https://
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).
------------------------------------------------------------------------
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
------------------------------------------------------------------------
-------------------------------------------------------------------------
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
