Federal Register / Vol. 78, No. 6 / Wednesday, January 9, 2013 / Rules and Regulations 1735 

TABLE 1 TO PARAGRAPH (e) FOR TAE 

125–01 ENGINES—Continued 

Software mapping Part No. 

T14V292DIA ................. 50–7610–55105R9. 

R28V292DIA ................ 50–7610–55107R5. 

TABLE 2 TO PARAGRAPH (e) FOR TAE 

125–02–99 ENGINES

Software mapping Part No. 

O14V301CES ............... 20–7610–E000110. 

O28V301CES ............... 20–7610–E001110. 

O14V301PIP ................ 40–7610–E000110. 

O28V301PIP ................ 40–7610–E001110. 

O14V301APEX ............. 60–7610–E000110. 

O14V301DA40 ............. 50–7610–E000110. 

O28V301DA42 ............. 52–7610–E000505. 

TABLE 3 TO PARAGRAPH (e) FOR TAE 

125–02–114 ENGINES

Software mapping Part No. 

P14V302CES ............... 20–7610–E002007. 

P28V302CES ............... 20–7610–E003007. 

P28V302PIP ................. 40–7610–E003007. 

P14V302APEX ............. 60–7610–E002007. 

P14V302DA40 .............. 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. 

(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. 

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 

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 

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: 


srobinson on DSK4SPTVN1PROD with 
1736 Federal Register / Vol. 78, No. 6 / Wednesday, January 9, 2013 / Rules and Regulations 

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: 


srobinson on DSK4SPTVN1PROD with 
Federal Register / Vol. 78, No. 6 / Wednesday, January 9, 2013 / Rules and Regulations 1737 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Indicated altitude test .................................... 2 work-hours × $85 per hour = $170 ........... $0 $170 Up to $15,300. 

Removal ........................................................ 2 work-hours × $85 per hour = $170 ........... 0 170 Up to $15,300. 

Pitot static certification test ........................... 3 work-hours × $85 per hour = $255 ........... 0 255 Up to $22,950. 

ADM check or test ......................................... 2 work-hours × $85 per hour = $170 ........... 0 170 Up to $15,300. 

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

Action Labor cost Parts cost Cost per 

product 

Pressure sensor test .................................................... 2 work-hours × $85 per hour = $170 ........................... $0 $170 

Removal ........................................................................ 2 work-hours × $85 per hour = $170 ........................... 0 170 

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 

■ 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– 

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 


srobinson on DSK4SPTVN1PROD with 
1738 Federal Register / Vol. 78, No. 6 / Wednesday, January 9, 2013 / Rules and Regulations 

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.

Honeywell Aerospace, 23500 West 105th Street, Olathe, KS 66061. 

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, 1850 West Rose Garden Lane, Phoenix, AZ 

85027. 

(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 

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. 


srobinson on DSK4SPTVN1PROD with 
Federal Register / Vol. 78, No. 6 / Wednesday, January 9, 2013 / Rules and Regulations 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/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 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: 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. 

DATES: This AD is effective February 13, 

2013. 


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