```

[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]

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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.

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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 http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For 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 http://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 
http://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 http://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 http://www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this 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 http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this 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.
------------------------------------------------------------------------

    (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 http://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 http://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 http://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: http://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
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