Airworthiness Directives; Honeywell International Inc. Air Data Pressure Transducers, 1735-1739 [2012-31587]
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Federal Register / Vol. 78, No. 6 / Wednesday, January 9, 2013 / Rules and Regulations
TABLE 1 TO PARAGRAPH (e) FOR TAE
125–01 ENGINES—Continued
Software mapping
Part No.
T14V292DIA .................
R28V292DIA ................
50–7610–55105R9.
50–7610–55107R5.
TABLE 2 TO PARAGRAPH (e) FOR TAE
125–02–99 ENGINES
Issued in Burlington, Massachusetts, on
December 27, 2012.
Colleen M. D’Alessandro,
Assistant Manager, Engine & Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 2012–31605 Filed 1–8–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
Software mapping
Part No.
O14V301CES ...............
O28V301CES ...............
O14V301PIP ................
O28V301PIP ................
O14V301APEX .............
O14V301DA40 .............
O28V301DA42 .............
20–7610–E000110.
20–7610–E001110.
40–7610–E000110.
40–7610–E001110.
60–7610–E000110.
50–7610–E000110.
52–7610–E000505.
14 CFR Part 39
TABLE 3 TO PARAGRAPH (e) FOR TAE
125–02–114 ENGINES
Software mapping
Part No.
P14V302CES ...............
P28V302CES ...............
P28V302PIP .................
P14V302APEX .............
P14V302DA40 ..............
20–7610–E002007.
20–7610–E003007.
40–7610–E003007.
60–7610–E002007.
50–7610–E002007.
(f) Alternative Methods of Compliance
(AMOCs)
The Manager, Engine Certification Office,
FAA, may approve AMOCs for this AD. Use
the procedures found in 14 CFR 39.19 to
make your request.
srobinson on DSK4SPTVN1PROD with
(g) Related Information
(1) For more information about this AD,
contact Robert Green, Aerospace Engineer,
Engine Certification Office, FAA, Engine &
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
email: robert.green@faa.gov; phone: 781–
238–7754; fax: 781–238 7199.
(2) Refer to MCAI European Aviation
Safety Agency Airworthiness Directive No.
2012–0116, dated July 3, 2012, and Thielert
Aircraft Engines Service Bulletin TM TAE
000–0007, Revision 19, dated August 31,
2012, for related information.
(3) For service information identified in
this AD, contact Thielert Aircraft Engines
GmbH, Platanenstrasse 14 D–09350,
Lichtenstein, Germany, phone: +49–37204–
696–0; fax: +49–37204–696–55; email:
info@centurion-engines.com. You may view
this service information at the FAA, Engine
& Propeller Directorate, 12 New England
Executive Park, Burlington, MA. For
information on the availability of this
material at the FAA, call 781–238–7125.
(h) Material Incorporated by Reference
None.
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[Docket No. FAA–2012–1315; Directorate
Identifier 2012–NM–191–AD; Amendment
39–17310; AD 2012–26–15]
RIN 2120–AA64
Airworthiness Directives; Honeywell
International Inc. Air Data Pressure
Transducers
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Honeywell International Inc. air data
pressure transducers as installed on
various aircraft. This AD requires
various tests or checks of equipment
having certain air data pressure
transducers, and removal of equipment
if necessary. As an option to the tests or
checks, this AD allows removal of
affected equipment having certain air
data pressure transducers. This AD was
prompted by a report of a pressure
measurement error in the pressure
transducer used in various air data
systems, which translates into air data
parameter errors. We are issuing this AD
to detect and correct inaccuracies of the
pressure sensors, which could result in
altitude, computed airspeed, true
airspeed, and Mach computation errors.
These errors could reduce the ability of
the flightcrew to maintain the safe flight
of the aircraft and could result in
consequent loss of control of the
aircraft.
DATES: This AD is effective January 24,
2013.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of January 24, 2013.
We must receive comments on this
AD by February 25, 2013.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
SUMMARY:
PO 00000
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1735
• 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 Honeywell service information
identified in this AD, contact Honeywell
Aerospace, Technical Publications and
Distribution, M/S 2101–201, P.O. Box
52170, Phoenix, AZ 85072–2170;
telephone 602–365–5535; fax 602–365–
5577; Internet https://
www.honeywell.com. For Airbus service
information identified in this AD for
Model A330 series airplanes, contact
Airbus SAS—Airworthiness Office—
EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone
+33 5 61 93 36 96; fax +33 5 61 93 45
80; email airworthiness.A330–
A340@airbus.com; Internet https://
www.airbus.com. For Airbus service
information identified in this AD for
Model A318, A319, A320, and A321
series airplanes, contact Airbus,
Airworthiness Office—EAS, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
Internet https://www.airbus.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
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 AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Office (phone: 800–647–
5527) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Blake Higuchi, Aerospace Engineer,
Systems and Equipment Branch, ANM–
130L, FAA, Los Angeles Aircraft
Certification Office, 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5315; fax: 562–627–
5210; email: blake.higuchi@faa.gov.
SUPPLEMENTARY INFORMATION:
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Discussion
We received a report of a pressure
measurement error in the air data
pressure sensor used in various air data
systems, which translates into air data
parameter errors, possibly related to
sleeks (micro-scratches on the polished
glass tube pressure port) and the anodic
bond of the glass tube to the sensor die.
Errors in the pressure sensor
measurements could impact other
aircraft systems using the pressure
measurements. The primary concern is
the impact on the air data system and
the associated airspeed (Mach,
computed airspeed, and true airspeed)
and computations. This error in the
static pressure measurement will result
in a higher indicated altitude than the
actual altitude and a higher indicated
airspeed than actual airspeed. This error
in the pitot pressure sensor will result
in a lower indicated airspeed than
actual airspeed. The error in the
pressure sensor measurement is a result
of a leak within the pressure sensor’s
vacuum reference that is compared with
the actual applied pressure. This
condition, if not corrected, could reduce
the ability of the flightcrew to maintain
the safe flight of the aircraft and could
result in consequent loss of control of
the aircraft.
srobinson on DSK4SPTVN1PROD with
Relevant Service Information
We reviewed Honeywell Alert Service
Bulletin ADM/ADC/ADAHRS–34–A01,
dated November 6, 2012. This service
bulletin describes procedures for an
indicated altitude test of equipment
(i.e., air data modules (ADM), air data
computers, air data attitude heading
reference systems, and digital air data
computers) having certain air data
pressure transducers, repetitive pressure
sensor tests if necessary, and removal of
equipment if necessary. This service
bulletin also specifies optional actions,
including repetitive pitot-static
certification testing and removal of
equipment having certain air data
pressure transducers.
We have also reviewed Airbus Alert
Operators Transmission (AOT)
A34N001–12, including Appendices A
and B, dated November 15, 2012, for
Airbus Model A318/A319/A320/A321
series airplanes; and Airbus AOT
A34N001–12, including Appendices A
and B, dated November 15, 2012, for
Airbus Model A330 series airplanes.
These AOTs describe procedures for
doing a repetitive ADM check or a
functional test of the ADM accuracy,
and replacing the ADM if necessary.
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FAA’s Determination
We are issuing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of these same
type designs.
AD Requirements
This AD requires accomplishing the
actions specified in the service
information described previously,
except as discussed under ‘‘Differences
Between the AD and the Service
Information.’’ The AD also requires
sending the test or check results (both
pass and fail) to the FAA and
Honeywell.
Differences Between the AD and the
Service Information
The service information that follows
specifies certain corrective actions for
various conditions. However we differ
from these actions and conditions in
that this AD requires removing affected
equipment and returning the equipment
to Honeywell if those conditions are
found.
• Airbus Alert Operators
Transmission (AOT) A34N001–12,
including Appendices A and B, dated
November 15, 2012, for Airbus Model
A318/A319/A320/A321 series airplanes;
and Airbus AOT A34N001–12,
including Appendices A and B, dated
November 15, 2012, for Airbus Model
A330 series airplanes; specifies to
replace the ADM if the ADM check fails.
• Honeywell Service Bulletin ACM/
ADC/ADAHRS–34–A01, dated
November 6, 2012, specifies to refer to
‘‘applicable procedures’’ if the indicated
altitude test exceeds 75 feet (23 meters).
• Honeywell Service Bulletin ACM/
ADC/ADAHRS–34–A01, dated
November 6, 2012, specifies to remove
the affected equipment if the pressure
test is greater than 0.70 millibar (mB).
In addition, the service information
that follows is missing corrective
actions for certain conditions; however,
this AD requires removing affected
equipment and returning the equipment
to Honeywell for those conditions that
are missing corrective actions.
• Airbus Alert Operators
Transmission (AOT) A34N001–12,
including Appendices A and B, dated
November 15, 2012, for Airbus Model
A318/A319/A320/A321 series airplanes;
and Airbus AOT A34N001–12,
including Appendices A and B, dated
November 15, 2012, for Airbus Model
A330 series airplanes; does not specify
any corrective action if the functional
test of the ADM accuracy fails.
• Honeywell Service Bulletin ACM/
ADC/ADAHRS–34–A01, dated
PO 00000
Frm 00024
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November 6, 2012, does not specify any
corrective action if the pitot static
certification test fails.
Interim Action
We consider this AD interim action.
The manufacturer is currently
developing a modification that will
address the unsafe condition identified
in this AD. Once this modification is
developed, approved, and available, we
might consider additional rulemaking.
FAA’s Justification and Determination
of the Effective Date
An unsafe condition exists that
requires the immediate adoption of this
AD. The FAA has found that the risk to
the flying public justifies waiving notice
and comment prior to adoption of this
rule because inaccuracies of the
pressure sensors could result in altitude,
computed airspeed, true airspeed, and
Mach computation errors. These errors
could reduce the ability of the
flightcrew to maintain the safe flight of
the aircraft and could result in
consequent loss of control of the
aircraft. Therefore, we find that notice
and opportunity for prior public
comment are impracticable and that
good cause exists for making this
amendment effective in less than 30
days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety and
was not preceded by notice and an
opportunity for public comment.
However, we invite you to send any
written data, views, or arguments about
this AD. Send your comments to an
address listed under the ADDRESSES
section. Include the docket number
FAA–2012–1315 and Directorate
Identifier 2012–NM–191–AD at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
this AD. We will consider all comments
received by the closing date and may
amend this AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this AD.
Costs of Compliance
We estimate that this AD affects 90
appliances installed on, but not limited
to, various aircraft of U.S. registry.
We estimate the following costs to
comply with this AD:
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ESTIMATED COSTS
Action
Labor cost
Indicated altitude test ....................................
Removal ........................................................
Pitot static certification test ...........................
ADM check or test .........................................
We estimate the following costs to do
any necessary pressure sensor tests or
removals that would be required based
2
2
3
2
work-hours
work-hours
work-hours
work-hours
×
×
×
×
$85
$85
$85
$85
per
per
per
per
hour
hour
hour
hour
Cost per
product
Parts cost
=
=
=
=
$170
$170
$255
$170
...........
...........
...........
...........
on the results of the tests or checks. We
have no way of determining the number
$0
0
0
0
Cost on U.S.
operators
$170
170
255
170
Up
Up
Up
Up
to
to
to
to
$15,300.
$15,300.
$22,950.
$15,300.
of aircraft that might need these
pressure sensor tests or removals:
ON-CONDITION COSTS
Action
Labor cost
Pressure sensor test ....................................................
Removal ........................................................................
2 work-hours × $85 per hour = $170 ...........................
2 work-hours × $85 per hour = $170 ...........................
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.
srobinson on DSK4SPTVN1PROD with
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation
in Alaska, and
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(4) 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 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 adding
the following new airworthiness
directive (AD):
■
2012–26–15 Honeywell International Inc.:
Amendment 39–17310; Docket No.
FAA–2012–1315; Directorate Identifier
2012–NM–191–AD.
(a) Effective Date
This AD is effective January 24, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to air data pressure
transducers, as installed in air data
computers (ADC), air data modules (ADM),
air data attitude heading reference systems
(ADAHRS), and digital air data computers
(DADC) having the part numbers and serial
numbers identified in Honeywell Alert
Service Bulletin ADM/ADC/ADAHRS–34–
PO 00000
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Cost per
product
Parts cost
$0
0
$170
170
A01, dated November 6, 2012. This appliance
is installed on, but not limited to, the aircraft
specified in paragraphs (c)(1) through (c)(11)
of this AD.
(1) Airbus Model A318–111, –112, –121,
and –122 airplanes; Model A319–111, –112,
–113, –114, –115, –131, –132, and –133
airplanes; Model A320–111, –211, –212,
–214, –231, –232, and –233 airplanes; Model
A321–111, –112, –131, –211, –212, –213,
–231, and –232 airplanes; Model A330–223F,
–243F, –201, –202, –203, –223, –243, –301,
–302, –303, –321, –322, –323, –341, –342,
and –343 airplanes; and Model A340–211,
–212, –213, –311, –312, –313, –541, and –642
airplanes.
(2) AGUSTA S.p.A. Model AW139
helicopters.
(3) Bell Helicopter Textron Canada Limited
Model 429 helicopters.
(4) The Boeing Company Model 767–200,
–300, –300F, and –400ER series airplanes;
and Model 777–200, –200LR, –300, –300ER,
and 777F series airplanes.
(5) Cessna Aircraft Company Model 560XL
(560 Excel and 560 XLS) airplanes.
(6) Dassault Aviation Model MystereFalcon 900 airplanes and Model FALCON
2000 airplanes.
(7) Empresa Brasileira de Aeronautica S.A.
(Embraer) Model EMB–135BJ airplanes.
(8) Gulfstream Aerospace Corporation
Model GIV–X and GV–SP airplanes.
(9) Learjet Inc. Model 45 airplanes.
(10) Pilatus Aircraft LTD. Model PC–12/
47E airplanes.
(11) Viking Air Limited (Type Certificate
previously held by Bombardier Inc.; de
Havilland, Inc.) Model (Twin Otter) DHC–6–
400 airplanes.
(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 34, Navigation.
(e) Unsafe Condition
This AD was prompted by a report of a
pressure measurement error in the pressure
transducer used in various air data systems,
which translates into air data parameter
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errors. We are issuing this AD to detect and
correct inaccuracies of the pressure sensors,
which could result in altitude, computed
airspeed, true airspeed, and Mach
computation errors. These errors could
reduce the ability of the flightcrew to
maintain the safe flight of the aircraft and
could result in consequent loss of control of
the aircraft.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Actions
Within 30 days after the effective date of
this AD: Do the actions in either paragraph
(g)(1) or (g)(2) of this AD, except as provided
by paragraphs (h) and (i) of this AD.
(1) Remove the affected equipment (i.e.,
ADC, ADM, ADAHRS, and DADC), as
identified in paragraph (c) of this AD, and
return the equipment to Honeywell at the
applicable address specified in table 1 to
paragraphs (g)(1), (g)(2), (h)(1), (h)(2)(i),
(i)(1)(i), and (i)(2) of this AD. Before
continued operations, the operator must
ensure that all of the required equipment is
properly installed in the aircraft.
TABLE 1 TO PARAGRAPHS (g)(1), (g)(2), (h)(1), (h)(2)(i), (i)(1)(i), AND (i)(2) OF THIS AD—ADDRESSES FOR RETURNED
PARTS
For part numbers identified in—
Return parts to—
Tables 12 and 13 of Honeywell Service Bulletin ADM/ADC/ADAHRS–
34–A01, dated November 6, 2012.
Tables 2, 3, 4, 5, 6, 7, 8, 9, 10, 11, and 14 of Honeywell Service Bulletin ADM/ADC/ADAHRS–34–A01, dated November 6, 2012.
Honeywell Aerospace, 23500 West 105th Street, Olathe, KS 66061.
srobinson on DSK4SPTVN1PROD with
(2) Do a pitot-static certification test, and
repeat the test thereafter at intervals not to
exceed 30 days, in accordance with
paragraph 1.C.(4)(a)3 of Honeywell Alert
Service Bulletin ADM/ADC/ADAHRS–34–
A01, dated November 6, 2012. If any pitotstatic certification test fails, remove the
affected equipment (i.e., ADC, ADM,
ADAHRS, or DADC) and return the
equipment to Honeywell at the applicable
address specified in table 1 to paragraphs
(g)(1), (g)(2), (h)(1), (h)(2)(i), (i)(1)(i), and (i)(2)
of this AD. Before continued operations, the
operator must ensure that all of the required
equipment is properly installed in the
aircraft.
(h) Optional Actions for Certain The Boeing
Company Airplanes, Gulfstream Aerospace
Corporation Airplanes, and PILATUS
AIRCRAFT LTD., Airplanes
For The Boeing Company Model 777–200,
–200LR, –300, –300ER, and 777F series
airplanes; Gulfstream Aerospace Corporation
Model GIV–X and GV–SP airplanes; and
PILATUS AIRCRAFT LTD., Model PC–12/
47E airplanes: In lieu of doing the actions
required by paragraph (g) of this AD, within
30 days after the effective date of this AD, do
an indicated altitude test, in accordance with
the Accomplishment Instructions of
Honeywell Alert Service Bulletin ADM/ADC/
ADAHRS–34–A01, dated November 6, 2012.
(1) If the indicated altitude exceeds 75 feet
(23 meters) from the current aircraft
elevation, before further flight, remove the
affected equipment (i.e., ADC, ADM,
ADAHRS, or DADC) and return the
equipment to Honeywell at the applicable
address specified in table 1 to paragraphs
(g)(1), (g)(2), (h)(1), (h)(2)(i), (i)(1)(i), and (i)(2)
of this AD. Before continued operations, the
operator must ensure that all of the required
equipment is properly installed in the
aircraft.
(2) If the indicated altitude is equal to or
less than 75 feet (23 meters) of the aircraft
elevation, before further flight, do a pressure
sensor test, in accordance with the
Accomplishment Instructions of Honeywell
Alert Service Bulletin ADM/ADC/ADAHRS–
34–A01, dated November 6, 2012.
(i) If the pressure error is greater than 0.70
millibar (mB), before further flight, remove
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Honeywell Aerospace, 1850 West Rose Garden Lane, Phoenix, AZ
85027.
the affected equipment (i.e., ADC, ADM,
ADAHRS, or DADC) and return the
equipment to Honeywell at the applicable
address specified in table 1 to paragraphs
(g)(1), (g)(2), (h)(1), (h)(2)(i), (i)(1)(i), and (i)(2)
of this AD. Before continued operations, the
operator must ensure that all of the required
equipment is properly installed in the
aircraft.
(ii) If the pressure error is greater than 0.50
mB, but less than or equal to 0.70 mB, repeat
the test within 30 days after the most recent
test.
(iii) If the pressure error is greater than or
equal to 0.25 mB, but less than or equal to
0.50 mB, repeat the test within 120 days after
the most recent test.
(i) Optional Actions for Certain Airbus
Airplanes
For Airbus Model A318, A319, A320, and
A321 airplanes having a manufacturer serial
number (MSN) and an ADM identified in
Appendix A of Airbus Alert Operators
Transmission (AOT) A34N001–12, including
Appendices A and B, dated November 15,
2012, for Airbus Model A318/A319/A320/
A321 series airplanes; and for Airbus Model
A330 series airplanes having an MSN and
ADM identified in Appendix A of Airbus
AOT A34N001–12, including Appendices A
and B, dated November 15, 2012, for Airbus
Model A330 series airplanes: In lieu of doing
the actions required by paragraph (g) of this
AD, within 30 days after the effective date of
this AD, do the actions specified in
paragraph (i)(1) or (i)(2) of this AD.
(1) Do an ADM check to determine the raw
pressure data values from integrated standby
instrument system (ISIS) and the affected
ADMs, in accordance with Appendix B, ‘‘Air
Data Module Check Procedure and Reporting
Table,’’ of Airbus AOT A34N001–12,
including Appendices A and B, dated
November 15, 2012, for Airbus Model A318/
A319/A320/A321 series airplanes; or Airbus
AOT A34N001–12, including Appendices A
and B, dated November 15, 2012, for Airbus
Model A330 series airplanes. These checks
must be performed by authorized
maintenance personnel.
(i) If ‘‘P_ISIS—P_ADM’’ is greater than 22,
before further flight, remove the affected
PO 00000
Frm 00026
Fmt 4700
Sfmt 4700
ADM and return the ADM to Honeywell at
the applicable address specified in table 1 to
paragraphs (g)(1), (g)(2), (h)(1), (h)(2)(i),
(i)(1)(i), and (i)(2) of this AD. Before
continued operations, the operator must
ensure that all of the required equipment is
properly installed in the aircraft.
(ii) If ‘‘P_ISIS—P_ADM’’ is greater than or
equal to 16, but equal to or less than 22,
within 30 days after the most recent check,
do the ADM check specified in paragraph
(i)(1) of this AD.
(iii) If ‘‘P_ISIS—P_ADM’’ is less than 16,
within 120 days after the most recent check,
do the ADM check specified in paragraph
(i)(1) of this AD.
(2) Perform a functional test of the ADM
accuracy, in accordance with Airbus AOT
A34N001–12, including Appendices A and
B, dated November 15, 2012, for Airbus
Model A318/A319/A320/A321 series
airplanes; or Airbus AOT A34N001–12,
including Appendices A and B, dated
November 15, 2012, for Airbus Model A330
series airplanes. Repeat the test thereafter at
intervals not to exceed 30 days. If any test
fails, before further flight, remove the
affected ADM and return the ADM to
Honeywell at the applicable address
specified in table 1 to paragraphs (g)(1),
(g)(2), (h)(1), (h)(2)(i), (i)(1)(i), and (i)(2) of
this AD. Before continued operations, the
operator must ensure that all of the required
equipment is properly installed in the
aircraft.
(j) Reporting
(1) For any airplane on which any test
specified in paragraph (h) of this AD has
been done: At the applicable time specified
in paragraph (j)(1)(i) or (j)(1)(ii) of this AD,
submit a report of the findings (both pass and
fail) of the test specified in paragraph (h) of
this AD to Honeywell by email
AeroTechSupport@honeywell.com or fax
602–365–1871. The report must include the
information specified in Appendix A of
Honeywell Alert Service Bulletin ADM/ADC/
ADAHRS–34–A01, dated November 6, 2012.
(i) If the test was done on or after the
effective date of this AD: Submit the report
within 15 days after the test.
E:\FR\FM\09JAR1.SGM
09JAR1
Federal Register / Vol. 78, No. 6 / Wednesday, January 9, 2013 / Rules and Regulations
(ii) If the test was done before the effective
date of this AD: Submit the report within 15
days after the effective date of this AD.
(2) For any airplane on which any test
specified in paragraph (h) of this AD, or any
check specified in paragraph (i)(1) of this AD,
has been done: At the applicable time
specified in paragraph (j)(2)(i) or (j)(2)(ii) of
this AD, submit a report of the findings (both
pass and fail) of the test specified in
paragraph (h) of this AD; or the check
specified in paragraph (i)(1) of this AD; as
applicable; to the Manager, Los Angeles
Aircraft Certification Office (ACO), FAA,
3960 Paramount Boulevard, Lakewood, CA
90712–4137.
(i) If the test or check was done on or after
the effective date of this AD: Submit the
report within 15 days after the test or check.
(ii) If the test or check was done before the
effective date of this AD: Submit the report
within 15 days after the effective date of this
AD.
(3) For Airbus Model A318, A319, A320,
A321, A330–200 Freighter, A330–200, and
A330–300 series airplanes: At the applicable
time specified in paragraph (j)(3)(i) or
(j)(3)(ii) of this AD, submit a report of the
findings (both pass and fail) of the check
required by paragraph (i)(1) of this AD to
Honeywell by email
AeroTechSupport@honeywell.com or fax
602–365–1871. The report must include the
information specified in the reporting sheet
in Appendix B, ‘‘Air Data Module Check
Procedure and Reporting Table,’’ of Airbus
AOT A34N001–12, including Appendices A
and B, dated November 15, 2012, for Airbus
Model A318/A319/A320/A321 series
airplanes; or Airbus AOT A34N001–12,
including Appendices A and B, dated
November 15, 2012, for Airbus Model A330
series airplanes.
(i) If the check was done on or after the
effective date of this AD: Submit the report
within 15 days after the check.
(ii) If the check was done before the
effective date of this AD: Submit the report
within 15 days after the effective date of this
AD.
srobinson on DSK4SPTVN1PROD with
(k) Parts Installation Limitation
As of the effective date of this AD, no
person may install air data pressure
transducers in air data computers, air data
modules, air data attitude heading reference
systems, and digital air data computers,
having the part numbers and serial numbers
identified in Honeywell Alert Service
Bulletin ADM/ADC/ADAHRS–34–A01, dated
November 6, 2012, on any aircraft.
(l) Paperwork Reduction Act Burden
Statement
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject to
a penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork Reduction
Act unless that collection of information
displays a current valid OMB Control
Number. The OMB Control Number for this
information collection is 2120–0056. Public
reporting for this collection of information is
estimated to be approximately 5 minutes per
VerDate Mar<15>2010
16:13 Jan 08, 2013
Jkt 229001
response, including the time for reviewing
instructions, completing and reviewing the
collection of information. All responses to
this collection of information are mandatory.
Comments concerning the accuracy of this
burden and suggestions for reducing the
burden should be directed to the FAA at: 800
Independence Ave. SW., Washington, DC
20591, Attn: Information Collection
Clearance Officer, AES–200.
(m) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Los Angeles ACO, FAA,
has the authority to approve AMOCs for this
AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal
inspector or local Flight Standards District
Office, as appropriate. If sending information
directly to the manager of the ACO, send it
to the attention of the person identified in the
Related Information section of this AD.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(n) Related Information
For more information about this AD,
contact Blake Higuchi, Aerospace Engineer,
Systems and Equipment Branch, ANM–130L,
FAA, Los Angeles ACO, 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5315; fax: 562–627–5210;
email: blake.higuchi@faa.gov.
(o) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Honeywell Alert Service Bulletin ADM/
ADC/ADAHRS–34–A01, dated November 6,
2012.
(ii) Airbus Alert Operators Transmission
(AOT) A34N001–12, including Appendices A
and B, dated November 15, 2012, for Airbus
Model A318/A319/A320/A321 series
airplanes.
(iii) Airbus AOT A34N001–12, including
Appendices A and B, dated November 15,
2012, for Airbus Model A330 series
airplanes.
(3) For Honeywell service information
identified in this AD, contact Honeywell
Aerospace, Technical Publications and
Distribution, M/S 2101–201, P.O. Box 52170,
Phoenix, AZ 85072–2170; telephone 602–
365–5535; fax 602–365–5577; Internet https://
www.honeywell.com. For Airbus service
information identified in this AD for Model
A330 series airplanes, contact Airbus SAS—
Airworthiness Office—EAL, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
France; telephone +33 5 61 93 36 96; fax +33
5 61 93 45 80; email airworthiness.A330–
A340@airbus.com; Internet https://
www.airbus.com. For Airbus service
information identified in this AD for Model
A318, A319, A320, and A321 series
airplanes, contact Airbus, Airworthiness
PO 00000
Frm 00027
Fmt 4700
Sfmt 4700
1739
Office—EAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com; Internet
https://www.airbus.com.
(4) You may view this service information
at FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on
December 21, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2012–31587 Filed 1–8–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–0632; Directorate
Identifier 2011–SW–044–AD; Amendment
39–17305; AD 2012–26–10]
RIN 2120–AA64
Airworthiness Directives; Eurocopter
France Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Eurocopter France (Eurocopter) Model
SA–365N, SA–365N1, AS–365N2, AS
365 N3, EC 155B, EC155B1, SA–365C,
SA–365C1, SA–365C2, and SA–366G1
helicopters. This AD requires inspecting
portions of the main gearbox (MGB) for
the presence of sealing compound and
corrosion. This AD was prompted by
reports of corrosion on the main MGB
casing lower area between the two
servo-control anchoring fitting
attachment ribs. An investigation
determined that the corrosion was
associated with sealing compound on
the lower part of the fitting/casing
attachment. The actions in this AD are
intended to detect corrosion on the
MGB casing, which could lead to a
crack, failure of the MGB, and
subsequent loss of control of the
helicopter.
SUMMARY:
DATES:
This AD is effective February 13,
2013.
E:\FR\FM\09JAR1.SGM
09JAR1
]]>Agencies
[Federal Register Volume 78, Number 6 (Wednesday, January 9, 2013)]
[Rules and Regulations]
[Pages 1735-1739]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-31587]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-1315; Directorate Identifier 2012-NM-191-AD;
Amendment 39-17310; AD 2012-26-15]
RIN 2120-AA64
Airworthiness Directives; Honeywell International Inc. Air Data
Pressure Transducers
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Honeywell International Inc. air data pressure transducers as installed
on various aircraft. This AD requires various tests or checks of
equipment having certain air data pressure transducers, and removal of
equipment if necessary. As an option to the tests or checks, this AD
allows removal of affected equipment having certain air data pressure
transducers. This AD was prompted by a report of a pressure measurement
error in the pressure transducer used in various air data systems,
which translates into air data parameter errors. We are issuing this AD
to detect and correct inaccuracies of the pressure sensors, which could
result in altitude, computed airspeed, true airspeed, and Mach
computation errors. These errors could reduce the ability of the
flightcrew to maintain the safe flight of the aircraft and could result
in consequent loss of control of the aircraft.
DATES: This AD is effective January 24, 2013.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of January 24,
2013.
We must receive comments on this AD by February 25, 2013.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://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 Honeywell service information identified in this AD, contact
Honeywell Aerospace, Technical Publications and Distribution, M/S 2101-
201, P.O. Box 52170, Phoenix, AZ 85072-2170; telephone 602-365-5535;
fax 602-365-5577; Internet https://www.honeywell.com. For Airbus service
information identified in this AD for Model A330 series airplanes,
contact Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax
+33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet
https://www.airbus.com. For Airbus service information identified in
this AD for Model A318, A319, A320, and A321 series airplanes, contact
Airbus, Airworthiness Office--EAS, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44
51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://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 AD, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Office (phone: 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Blake Higuchi, Aerospace Engineer,
Systems and Equipment Branch, ANM-130L, FAA, Los Angeles Aircraft
Certification Office, 3960 Paramount Boulevard, Lakewood, CA 90712-
4137; phone: 562-627-5315; fax: 562-627-5210; email:
blake.higuchi@faa.gov.
SUPPLEMENTARY INFORMATION:
[[Page 1736]]
Discussion
We received a report of a pressure measurement error in the air
data pressure sensor used in various air data systems, which translates
into air data parameter errors, possibly related to sleeks (micro-
scratches on the polished glass tube pressure port) and the anodic bond
of the glass tube to the sensor die. Errors in the pressure sensor
measurements could impact other aircraft systems using the pressure
measurements. The primary concern is the impact on the air data system
and the associated airspeed (Mach, computed airspeed, and true
airspeed) and computations. This error in the static pressure
measurement will result in a higher indicated altitude than the actual
altitude and a higher indicated airspeed than actual airspeed. This
error in the pitot pressure sensor will result in a lower indicated
airspeed than actual airspeed. The error in the pressure sensor
measurement is a result of a leak within the pressure sensor's vacuum
reference that is compared with the actual applied pressure. This
condition, if not corrected, could reduce the ability of the flightcrew
to maintain the safe flight of the aircraft and could result in
consequent loss of control of the aircraft.
Relevant Service Information
We reviewed Honeywell Alert Service Bulletin ADM/ADC/ADAHRS-34-A01,
dated November 6, 2012. This service bulletin describes procedures for
an indicated altitude test of equipment (i.e., air data modules (ADM),
air data computers, air data attitude heading reference systems, and
digital air data computers) having certain air data pressure
transducers, repetitive pressure sensor tests if necessary, and removal
of equipment if necessary. This service bulletin also specifies
optional actions, including repetitive pitot-static certification
testing and removal of equipment having certain air data pressure
transducers.
We have also reviewed Airbus Alert Operators Transmission (AOT)
A34N001-12, including Appendices A and B, dated November 15, 2012, for
Airbus Model A318/A319/A320/A321 series airplanes; and Airbus AOT
A34N001-12, including Appendices A and B, dated November 15, 2012, for
Airbus Model A330 series airplanes. These AOTs describe procedures for
doing a repetitive ADM check or a functional test of the ADM accuracy,
and replacing the ADM if necessary.
FAA's Determination
We are issuing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of these same type
designs.
AD Requirements
This AD requires accomplishing the actions specified in the service
information described previously, except as discussed under
``Differences Between the AD and the Service Information.'' The AD also
requires sending the test or check results (both pass and fail) to the
FAA and Honeywell.
Differences Between the AD and the Service Information
The service information that follows specifies certain corrective
actions for various conditions. However we differ from these actions
and conditions in that this AD requires removing affected equipment and
returning the equipment to Honeywell if those conditions are found.
Airbus Alert Operators Transmission (AOT) A34N001-12,
including Appendices A and B, dated November 15, 2012, for Airbus Model
A318/A319/A320/A321 series airplanes; and Airbus AOT A34N001-12,
including Appendices A and B, dated November 15, 2012, for Airbus Model
A330 series airplanes; specifies to replace the ADM if the ADM check
fails.
Honeywell Service Bulletin ACM/ADC/ADAHRS-34-A01, dated
November 6, 2012, specifies to refer to ``applicable procedures'' if
the indicated altitude test exceeds 75 feet (23 meters).
Honeywell Service Bulletin ACM/ADC/ADAHRS-34-A01, dated
November 6, 2012, specifies to remove the affected equipment if the
pressure test is greater than 0.70 millibar (mB).
In addition, the service information that follows is missing
corrective actions for certain conditions; however, this AD requires
removing affected equipment and returning the equipment to Honeywell
for those conditions that are missing corrective actions.
Airbus Alert Operators Transmission (AOT) A34N001-12,
including Appendices A and B, dated November 15, 2012, for Airbus Model
A318/A319/A320/A321 series airplanes; and Airbus AOT A34N001-12,
including Appendices A and B, dated November 15, 2012, for Airbus Model
A330 series airplanes; does not specify any corrective action if the
functional test of the ADM accuracy fails.
Honeywell Service Bulletin ACM/ADC/ADAHRS-34-A01, dated
November 6, 2012, does not specify any corrective action if the pitot
static certification test fails.
Interim Action
We consider this AD interim action. The manufacturer is currently
developing a modification that will address the unsafe condition
identified in this AD. Once this modification is developed, approved,
and available, we might consider additional rulemaking.
FAA's Justification and Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because
inaccuracies of the pressure sensors could result in altitude, computed
airspeed, true airspeed, and Mach computation errors. These errors
could reduce the ability of the flightcrew to maintain the safe flight
of the aircraft and could result in consequent loss of control of the
aircraft. Therefore, we find that notice and opportunity for prior
public comment are impracticable and that good cause exists for making
this amendment effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment. However, we invite you to send any written data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include the docket number FAA-2012-1315 and
Directorate Identifier 2012-NM-191-AD at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this AD. We will
consider all comments received by the closing date and may amend this
AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.
Costs of Compliance
We estimate that this AD affects 90 appliances installed on, but
not limited to, various aircraft of U.S. registry.
We estimate the following costs to comply with this AD:
[[Page 1737]]
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Indicated altitude test.......... 2 work-hours x $85 $0 $170 Up to $15,300.
per hour = $170.
Removal.......................... 2 work-hours x $85 0 170 Up to $15,300.
per hour = $170.
Pitot static certification test.. 3 work-hours x $85 0 255 Up to $22,950.
per hour = $255.
ADM check or test................ 2 work-hours x $85 0 170 Up to $15,300.
per hour = $170.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary pressure sensor
tests or removals that would be required based on the results of the
tests or checks. We have no way of determining the number of aircraft
that might need these pressure sensor tests or removals:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Pressure sensor test.......................... 2 work-hours x $85 per hour = $0 $170
$170.
Removal....................................... 2 work-hours x $85 per hour = 0 170
$170.
----------------------------------------------------------------------------------------------------------------
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
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
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]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2012-26-15 Honeywell International Inc.: Amendment 39-17310; Docket
No. FAA-2012-1315; Directorate Identifier 2012-NM-191-AD.
(a) Effective Date
This AD is effective January 24, 2013.
(b) Affected ADs
None.
(c) Applicability
This AD applies to air data pressure transducers, as installed
in air data computers (ADC), air data modules (ADM), air data
attitude heading reference systems (ADAHRS), and digital air data
computers (DADC) having the part numbers and serial numbers
identified in Honeywell Alert Service Bulletin ADM/ADC/ADAHRS-34-
A01, dated November 6, 2012. This appliance is installed on, but not
limited to, the aircraft specified in paragraphs (c)(1) through
(c)(11) of this AD.
(1) Airbus Model A318-111, -112, -121, and -122 airplanes; Model
A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes;
Model A320-111, -211, -212, -214, -231, -232, and -233 airplanes;
Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes; Model A330-223F, -243F, -201, -202, -203, -223, -243, -
301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes;
and Model A340-211, -212, -213, -311, -312, -313, -541, and -642
airplanes.
(2) AGUSTA S.p.A. Model AW139 helicopters.
(3) Bell Helicopter Textron Canada Limited Model 429
helicopters.
(4) The Boeing Company Model 767-200, -300, -300F, and -400ER
series airplanes; and Model 777-200, -200LR, -300, -300ER, and 777F
series airplanes.
(5) Cessna Aircraft Company Model 560XL (560 Excel and 560 XLS)
airplanes.
(6) Dassault Aviation Model Mystere-Falcon 900 airplanes and
Model FALCON 2000 airplanes.
(7) Empresa Brasileira de Aeronautica S.A. (Embraer) Model EMB-
135BJ airplanes.
(8) Gulfstream Aerospace Corporation Model GIV-X and GV-SP
airplanes.
(9) Learjet Inc. Model 45 airplanes.
(10) Pilatus Aircraft LTD. Model PC-12/47E airplanes.
(11) Viking Air Limited (Type Certificate previously held by
Bombardier Inc.; de Havilland, Inc.) Model (Twin Otter) DHC-6-400
airplanes.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 34, Navigation.
(e) Unsafe Condition
This AD was prompted by a report of a pressure measurement error
in the pressure transducer used in various air data systems, which
translates into air data parameter
[[Page 1738]]
errors. We are issuing this AD to detect and correct inaccuracies of
the pressure sensors, which could result in altitude, computed
airspeed, true airspeed, and Mach computation errors. These errors
could reduce the ability of the flightcrew to maintain the safe
flight of the aircraft and could result in consequent loss of
control of the aircraft.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Actions
Within 30 days after the effective date of this AD: Do the
actions in either paragraph (g)(1) or (g)(2) of this AD, except as
provided by paragraphs (h) and (i) of this AD.
(1) Remove the affected equipment (i.e., ADC, ADM, ADAHRS, and
DADC), as identified in paragraph (c) of this AD, and return the
equipment to Honeywell at the applicable address specified in table
1 to paragraphs (g)(1), (g)(2), (h)(1), (h)(2)(i), (i)(1)(i), and
(i)(2) of this AD. Before continued operations, the operator must
ensure that all of the required equipment is properly installed in
the aircraft.
Table 1 to Paragraphs (g)(1), (g)(2), (h)(1), (h)(2)(i), (i)(1)(i), and
(i)(2) of This AD--Addresses for Returned Parts
------------------------------------------------------------------------
For part numbers identified in-- Return parts to--
------------------------------------------------------------------------
Tables 12 and 13 of Honeywell Service Honeywell Aerospace, 23500 West
Bulletin ADM/ADC/ADAHRS-34-A01, dated 105th Street, Olathe, KS
November 6, 2012. 66061.
Tables 2, 3, 4, 5, 6, 7, 8, 9, 10, 11, Honeywell Aerospace, 1850 West
and 14 of Honeywell Service Bulletin Rose Garden Lane, Phoenix, AZ
ADM/ADC/ADAHRS-34-A01, dated November 85027.
6, 2012.
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(2) Do a pitot-static certification test, and repeat the test
thereafter at intervals not to exceed 30 days, in accordance with
paragraph 1.C.(4)(a)3 of Honeywell Alert Service Bulletin ADM/ADC/
ADAHRS-34-A01, dated November 6, 2012. If any pitot-static
certification test fails, remove the affected equipment (i.e., ADC,
ADM, ADAHRS, or DADC) and return the equipment to Honeywell at the
applicable address specified in table 1 to paragraphs (g)(1),
(g)(2), (h)(1), (h)(2)(i), (i)(1)(i), and (i)(2) of this AD. Before
continued operations, the operator must ensure that all of the
required equipment is properly installed in the aircraft.
(h) Optional Actions for Certain The Boeing Company Airplanes,
Gulfstream Aerospace Corporation Airplanes, and PILATUS AIRCRAFT LTD.,
Airplanes
For The Boeing Company Model 777-200, -200LR, -300, -300ER, and
777F series airplanes; Gulfstream Aerospace Corporation Model GIV-X
and GV-SP airplanes; and PILATUS AIRCRAFT LTD., Model PC-12/47E
airplanes: In lieu of doing the actions required by paragraph (g) of
this AD, within 30 days after the effective date of this AD, do an
indicated altitude test, in accordance with the Accomplishment
Instructions of Honeywell Alert Service Bulletin ADM/ADC/ADAHRS-34-
A01, dated November 6, 2012.
(1) If the indicated altitude exceeds 75 feet (23 meters) from
the current aircraft elevation, before further flight, remove the
affected equipment (i.e., ADC, ADM, ADAHRS, or DADC) and return the
equipment to Honeywell at the applicable address specified in table
1 to paragraphs (g)(1), (g)(2), (h)(1), (h)(2)(i), (i)(1)(i), and
(i)(2) of this AD. Before continued operations, the operator must
ensure that all of the required equipment is properly installed in
the aircraft.
(2) If the indicated altitude is equal to or less than 75 feet
(23 meters) of the aircraft elevation, before further flight, do a
pressure sensor test, in accordance with the Accomplishment
Instructions of Honeywell Alert Service Bulletin ADM/ADC/ADAHRS-34-
A01, dated November 6, 2012.
(i) If the pressure error is greater than 0.70 millibar (mB),
before further flight, remove the affected equipment (i.e., ADC,
ADM, ADAHRS, or DADC) and return the equipment to Honeywell at the
applicable address specified in table 1 to paragraphs (g)(1),
(g)(2), (h)(1), (h)(2)(i), (i)(1)(i), and (i)(2) of this AD. Before
continued operations, the operator must ensure that all of the
required equipment is properly installed in the aircraft.
(ii) If the pressure error is greater than 0.50 mB, but less
than or equal to 0.70 mB, repeat the test within 30 days after the
most recent test.
(iii) If the pressure error is greater than or equal to 0.25 mB,
but less than or equal to 0.50 mB, repeat the test within 120 days
after the most recent test.
(i) Optional Actions for Certain Airbus Airplanes
For Airbus Model A318, A319, A320, and A321 airplanes having a
manufacturer serial number (MSN) and an ADM identified in Appendix A
of Airbus Alert Operators Transmission (AOT) A34N001-12, including
Appendices A and B, dated November 15, 2012, for Airbus Model A318/
A319/A320/A321 series airplanes; and for Airbus Model A330 series
airplanes having an MSN and ADM identified in Appendix A of Airbus
AOT A34N001-12, including Appendices A and B, dated November 15,
2012, for Airbus Model A330 series airplanes: In lieu of doing the
actions required by paragraph (g) of this AD, within 30 days after
the effective date of this AD, do the actions specified in paragraph
(i)(1) or (i)(2) of this AD.
(1) Do an ADM check to determine the raw pressure data values
from integrated standby instrument system (ISIS) and the affected
ADMs, in accordance with Appendix B, ``Air Data Module Check
Procedure and Reporting Table,'' of Airbus AOT A34N001-12, including
Appendices A and B, dated November 15, 2012, for Airbus Model A318/
A319/A320/A321 series airplanes; or Airbus AOT A34N001-12, including
Appendices A and B, dated November 15, 2012, for Airbus Model A330
series airplanes. These checks must be performed by authorized
maintenance personnel.
(i) If ``P--ISIS--P--ADM'' is greater than 22, before further
flight, remove the affected ADM and return the ADM to Honeywell at
the applicable address specified in table 1 to paragraphs (g)(1),
(g)(2), (h)(1), (h)(2)(i), (i)(1)(i), and (i)(2) of this AD. Before
continued operations, the operator must ensure that all of the
required equipment is properly installed in the aircraft.
(ii) If ``P--ISIS--P--ADM'' is greater than or equal to 16, but
equal to or less than 22, within 30 days after the most recent
check, do the ADM check specified in paragraph (i)(1) of this AD.
(iii) If ``P--ISIS--P--ADM'' is less than 16, within 120 days
after the most recent check, do the ADM check specified in paragraph
(i)(1) of this AD.
(2) Perform a functional test of the ADM accuracy, in accordance
with Airbus AOT A34N001-12, including Appendices A and B, dated
November 15, 2012, for Airbus Model A318/A319/A320/A321 series
airplanes; or Airbus AOT A34N001-12, including Appendices A and B,
dated November 15, 2012, for Airbus Model A330 series airplanes.
Repeat the test thereafter at intervals not to exceed 30 days. If
any test fails, before further flight, remove the affected ADM and
return the ADM to Honeywell at the applicable address specified in
table 1 to paragraphs (g)(1), (g)(2), (h)(1), (h)(2)(i), (i)(1)(i),
and (i)(2) of this AD. Before continued operations, the operator
must ensure that all of the required equipment is properly installed
in the aircraft.
(j) Reporting
(1) For any airplane on which any test specified in paragraph
(h) of this AD has been done: At the applicable time specified in
paragraph (j)(1)(i) or (j)(1)(ii) of this AD, submit a report of the
findings (both pass and fail) of the test specified in paragraph (h)
of this AD to Honeywell by email AeroTechSupport@honeywell.com or
fax 602-365-1871. The report must include the information specified
in Appendix A of Honeywell Alert Service Bulletin ADM/ADC/ADAHRS-34-
A01, dated November 6, 2012.
(i) If the test was done on or after the effective date of this
AD: Submit the report within 15 days after the test.
[[Page 1739]]
(ii) If the test was done before the effective date of this AD:
Submit the report within 15 days after the effective date of this
AD.
(2) For any airplane on which any test specified in paragraph
(h) of this AD, or any check specified in paragraph (i)(1) of this
AD, has been done: At the applicable time specified in paragraph
(j)(2)(i) or (j)(2)(ii) of this AD, submit a report of the findings
(both pass and fail) of the test specified in paragraph (h) of this
AD; or the check specified in paragraph (i)(1) of this AD; as
applicable; to the Manager, Los Angeles Aircraft Certification
Office (ACO), FAA, 3960 Paramount Boulevard, Lakewood, CA 90712-
4137.
(i) If the test or check was done on or after the effective date
of this AD: Submit the report within 15 days after the test or
check.
(ii) If the test or check was done before the effective date of
this AD: Submit the report within 15 days after the effective date
of this AD.
(3) For Airbus Model A318, A319, A320, A321, A330-200 Freighter,
A330-200, and A330-300 series airplanes: At the applicable time
specified in paragraph (j)(3)(i) or (j)(3)(ii) of this AD, submit a
report of the findings (both pass and fail) of the check required by
paragraph (i)(1) of this AD to Honeywell by email
AeroTechSupport@honeywell.com or fax 602-365-1871. The report must
include the information specified in the reporting sheet in Appendix
B, ``Air Data Module Check Procedure and Reporting Table,'' of
Airbus AOT A34N001-12, including Appendices A and B, dated November
15, 2012, for Airbus Model A318/A319/A320/A321 series airplanes; or
Airbus AOT A34N001-12, including Appendices A and B, dated November
15, 2012, for Airbus Model A330 series airplanes.
(i) If the check was done on or after the effective date of this
AD: Submit the report within 15 days after the check.
(ii) If the check was done before the effective date of this AD:
Submit the report within 15 days after the effective date of this
AD.
(k) Parts Installation Limitation
As of the effective date of this AD, no person may install air
data pressure transducers in air data computers, air data modules,
air data attitude heading reference systems, and digital air data
computers, having the part numbers and serial numbers identified in
Honeywell Alert Service Bulletin ADM/ADC/ADAHRS-34-A01, dated
November 6, 2012, on any aircraft.
(l) Paperwork Reduction Act Burden Statement
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to a penalty
for failure to comply with a collection of information subject to
the requirements of the Paperwork Reduction Act unless that
collection of information displays a current valid OMB Control
Number. The OMB Control Number for this information collection is
2120-0056. Public reporting for this collection of information is
estimated to be approximately 5 minutes per response, including the
time for reviewing instructions, completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Comments concerning the accuracy of this
burden and suggestions for reducing the burden should be directed to
the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer, AES-200.
(m) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Los Angeles ACO, FAA, has the authority to
approve AMOCs for this AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request
to your principal inspector or local Flight Standards District
Office, as appropriate. If sending information directly to the
manager of the ACO, send it to the attention of the person
identified in the Related Information section of this AD.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(n) Related Information
For more information about this AD, contact Blake Higuchi,
Aerospace Engineer, Systems and Equipment Branch, ANM-130L, FAA, Los
Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712-4137;
phone: 562-627-5315; fax: 562-627-5210; email:
blake.higuchi@faa.gov.
(o) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Honeywell Alert Service Bulletin ADM/ADC/ADAHRS-34-A01,
dated November 6, 2012.
(ii) Airbus Alert Operators Transmission (AOT) A34N001-12,
including Appendices A and B, dated November 15, 2012, for Airbus
Model A318/A319/A320/A321 series airplanes.
(iii) Airbus AOT A34N001-12, including Appendices A and B, dated
November 15, 2012, for Airbus Model A330 series airplanes.
(3) For Honeywell service information identified in this AD,
contact Honeywell Aerospace, Technical Publications and
Distribution, M/S 2101-201, P.O. Box 52170, Phoenix, AZ 85072-2170;
telephone 602-365-5535; fax 602-365-5577; Internet https://www.honeywell.com. For Airbus service information identified in this
AD for Model A330 series airplanes, contact Airbus SAS--
Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93
45 80; email airworthiness.A330-A340@airbus.com; Internet https://www.airbus.com. For Airbus service information identified in this AD
for Model A318, A319, A320, and A321 series airplanes, contact
Airbus, Airworthiness Office--EAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com.
(4) You may view this service information at FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on December 21, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-31587 Filed 1-8-13; 8:45 am]
BILLING CODE 4910-13-P
