Federal Register / Vol. 78, No. 61 / Friday, March 29, 2013 / Rules and Regulations 19085 

was listed in accordance with 

§ 94.6(a)(2)(i) as one in which HPAI is 

considered to exist, except for the 

APHIS-defined EU Poultry Trade 

Region; 

(ii) A restricted zone in the APHISdefined EU Poultry Trade Region 

established because of detection of 

Newcastle disease or HPAI in 

commercial poultry, from the time of 

detection until the designation of the 

zone as a restricted zone is removed by 

the competent veterinary authority of 

the Member State or until 3 months (90 

days) following depopulation of the 

poultry on affected premises in the 

restricted zone and the cleaning and 

disinfection of the last affected premises 

in the zone, whichever is later; or 

(iii) A restricted zone in the APHISdefined EU Poultry Trade Region 

established because of detection of 

Newcastle disease or HPAI in racing 

pigeons, backyard flocks, and wild 

birds, from the time of detection until 

the designation of the zone as a 

restricted zone is removed by the 

competent veterinary authority of the 

Member State. 

(2) The birds and poultry must not 

have been commingled with other birds 

or poultry that have at any time been in 

any of the regions or zones described in 

paragraphs (b)(1)(i) through (b)(1)(iii) of 

this section. 

(3) The birds and poultry must only 

originate from within the APHISdefined EU Poultry Trade Region and 

the farms of origin must not have 

received birds or poultry imported from 

outside the APHIS-defined EU Poultry 

Trade Region. 

(4) No equipment or materials used in 

transporting the birds and poultry may 

have been used previously for 

transporting birds or poultry that do not 

meet the requirements of this paragraph, 

unless the equipment and materials 

have first been cleaned and disinfected. 

(5) The birds and poultry must be 

accompanied by a certificate issued by 

an official of the competent veterinary 

authority of the Member State who is 

authorized to issue the inspection 

certificate required by § 93.205 of this 

subchapter, stating that the applicable 

provisions of paragraphs (b)(1) through 

(b)(4) of this section have been met. The 

certification may be placed on the 

foreign meat inspection certificate 

required by § 381.196 of this title or may 

be contained in a separate document. 

(c) Hatching eggs. Hatching eggs 

intended for import from the APHISdefined EU Poultry Trade Region are 

subject to all applicable provisions of 

paragraph (b) of this section, except that 

such hatching eggs may be moved 

through zones established because of 

detection of HPAI within the APHISdefined EU Poultry Trade Region 

provided that the hatching eggs are 

transported under official seal and 

accompanied by a certificate as 

indicated in § 94.28(b)(5) stating that the 

applicable provisions of paragraph (b) 

have been met. The import permit will 

require the seal number to be listed on 

the health certificate that accompanies 

the shipment and the veterinarian who 

places the seal will be required to sign 

his or her name under the seal number. 

Seals must not be broken until the 

shipment reaches its U.S. port of entry. 

Hatching egg shipment with seals that 

are not intact will be rejected upon 

inspection at the U.S. port of entry. 

(d) Presentation of certificates. The 

certificates required by paragraphs 

(a)(5), (b)(5), and (c) of this section must 

be presented by the importer to an 

authorized inspector at the port of 

arrival, upon arrival of the birds, 

poultry, hatching eggs, or poultry meat 

and products at the port. 

PART 95—SANITARY CONTROL OF 

ANIMAL BYPRODUCTS (EXCEPT 

CASINGS), AND HAY AND STRAW, 

OFFERED FOR ENTRY INTO THE 

UNITED STATES 

■ 23. The authority citation for part 95 

continues to read as follows: 

Authority: 7 U.S.C. 8301–8317; 21 U.S.C. 

136 and 136a; 31 U.S.C. 9701; 7 CFR 2.22, 

2.80, and 371.4. 

§ 95.5 [Amended] 

■ 24. In § 95.5, paragraph (c) is amended 

by removing the words ‘‘exotic’’ and 

‘‘subtype H5N1’’. 

§ 95.6 [Amended] 

■ 25. In § 95.6, paragraph (c) is amended 

by removing the word ‘‘exotic’’. 

PART 104—PERMITS FOR 

BIOLOGICAL PRODUCTS 

■ 26. The authority citation for part 104 

continues to read as follows: 

Authority: 21 U.S.C. 151–159; 7 CFR 2.22, 

2.80, and 371.4. 

§ 104.2 [Amended] 

■ 27. In § 104.2, paragraph (b) is 

amended by removing the words ‘‘fowl 

pest (fowl plague)’’ and adding the 

words ‘‘highly pathogenic avian 

influenza’’ in their place. 

Done in Washington, DC, this 26th day of 

March 2013. 

Peter Fernandez, 

Acting Administrator, Animal and Plant 

Health Inspection Service. 

[FR Doc. 2013–07345 Filed 3–28–13; 8:45 am] 

BILLING CODE 3410–34–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0150; Directorate 

Identifier 2011–NM–234–AD; Amendment 

39–17399; AD 2013–06–03] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A318, A319, A320, and 

A321 series airplanes. This AD was 

prompted by reports of oil residue 

between the stator and the rotor parts of 

the position resolvers of the angle of 

attack (AOA) vane, which was a result 

of incorrect removal of the machining 

oil during the manufacturing process of 

the AOA resolvers. This AD requires an 

inspection to determine if certain AOA 

probes are installed, and replacement of 

any affected AOA probe. We are issuing 

this AD to prevent erroneous AOA 

information and consequent delayed or 

non-activation of the AOA protection 

systems, which during flight at a high 

AOA, could result in reduced control of 

the airplane. 

DATES: This AD becomes effective May 

3, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of May 3, 2013. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1405; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a second supplemental 

notice of proposed rulemaking (SNPRM) 

to amend 14 CFR part 39 to include an 

AD that would apply to the specified 

products. That second SNPRM was 

published in the Federal Register on 


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19086 Federal Register / Vol. 78, No. 61 / Friday, March 29, 2013 / Rules and Regulations 

December 10, 2012 (77 FR 73340). That 

second SNPRM proposed to correct an 

unsafe condition for the specified 

products. The Mandatory Continuing 

Airworthiness Information (MCAI) 

states: 

During Airbus Final Assembly Line flight 

tests, AoA [angle of attack] data from two 

different aeroplanes were found inaccurate, 

which was confirmed by flight data analysis. 

Investigation conducted by Airbus and 

Thales on the removed probes revealed oil 

residue between the stator and the rotor parts 

of the AoA vane position resolvers. This oil 

residue was the result of incorrect removal of 

machining oil during the manufacturing 

process of the AoA resolvers. At low 

temperatures, this oil residue becomes 

viscous (typically in cruise), causing delayed 

and/or reduced AoA vane movement. 

Multiple AOA probes could be 

simultaneously affected, providing incorrect 

indications of the AoA of the aeroplane. 

This condition, if not corrected, could lead 

to erroneous AoA information and 

consequent delayed or non-activation of the 

AoA protection systems which, during flight 

at a high angle of attack, could result in 

reduced control of the aeroplane. 

For the reasons described above, this 

[European Aviation Safety Agency (EASA)] 

AD requires the identification of the serial 

number (s/n) of each installed Thales 

Avionics Part Number (P/N) C16291AA AoA 

probe and the replacement of all suspect 

units with serviceable ones. This AD also 

prohibits the (re)installation of these same 

s/n probes on any aeroplane, unless 

corrective measures have been accomplished. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. 

Request to Update Service Information 

Airbus requested that the service 

information referenced in the second 

SNPRM (77 FR 73340, December 10, 

2012) be updated to include recently 

added service information. Airbus 

stated that EASA has issued AD 2012– 

0236R1, dated December 17, 2012. In 

addition, Airbus stated that Thales 

Avionics has issued Service Bulletin 

C16291A–34–007, Revision 04, dated 

October 11, 2012. 

We partially agree with Airbus’ 

request regarding using the most recent 

service information. Since the second 

SNPRM (77 FR 73340, December 10, 

2012) was issued, we have reviewed 

Thales Avionics Service Bulletin 

C16291A–34–007, Revision 04, dated 

October 11, 2012. The actions in that 

service information remain unchanged 

from the previous service information. 

We have revised paragraphs (g), (i), and 

(k) of this AD accordingly to reflect the 

most current Thales Avionics service 

information. 

In addition, we have reviewed EASA 

AD 2012–0236, dated November 9, 2012 

(corrected November 12, 2012), and 

EASA AD 2012–0236R1, dated 

December 17, 2012. We have 

determined that no subsequent changes 

are required in this final rule as done to 

the EASA AD. We have not changed this 

final rule in this regard. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously– 

and minor editorial changes. We have 

determined that these changes: 

• Are consistent with the intent that 

was proposed in the second SNPRM (77 

FR 73340, December 10, 2012) for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM (77 FR 73340, 

December 10, 2012). 

Costs of Compliance 

We estimate that this AD will affect 

755 products of U.S. registry. We also 

estimate that it will take about 2 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this AD to the U.S. operators to 

be $128,350, or $170 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 3 work-hours and require parts 

costing $0, for a cost of $255 per 

product. We have no way of 

determining the number of products 

that may need these actions. 

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 

We determined that 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 the 

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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains the second SNPRM (77 FR 

73340, December 10, 2012), the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

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 AD: 


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Federal Register / Vol. 78, No. 61 / Friday, March 29, 2013 / Rules and Regulations 19087 

2013–06–03 Airbus: Amendment 39–17399. 

Docket No. FAA–2012–0150; Directorate 

Identifier 2011–NM–234–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective May 3, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all 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; and Model A321–111, –112, –131, 

–211, –212, –213, –231, and –232 airplanes; 

certificated in any category; all manufacturer 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 34: Navigation. 

(e) Reason 

This AD was prompted by reports of oil 

residue between the stator and the rotor parts 

of the position resolvers of the angle of attack 

(AOA) vane, which was a result of incorrect 

removal of the machining oil during the 

manufacturing process of the AOA resolvers. 

We are issuing this AD to prevent erroneous 

AOA information and consequent delayed or 

non-activation of the AOA protection 

systems, which during flight at a high angle 

of attack, could result in reduced control of 

the airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Inspection 

Within 12 months after the effective date 

of this AD, except as provided by paragraph 

(h) of this AD: Do the inspections specified 

in paragraphs (g)(1) and (g)(2) of this AD. 

(1) Inspect to determine the part number 

(P/N) and serial number of each Thales 

Avionics AOA probe, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–34–1452, dated 

January 29, 2010. If any probe is found 

having P/N C16291AA and having a serial 

number listed in Thales Avionics Service 

Bulletin C16291A–34–007, Revision 04, 

dated October 11, 2012: Within 12 months 

after the effective date of this AD, replace the 

AOA probe, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–34–1452, provided 

that Thales Avionics Service Bulletin 

C16291A–34–009, dated September 10, 2009; 

or Airbus Service Bulletin A320–34–1444, 

dated October 7, 2009; have not been 

accomplished. Thales Avionics Service 

Bulletin C16291A–34–009, dated September 

10, 2009; and Airbus Service Bulletin A320– 

34–1444, dated October 7, 2009; (which are 

not incorporated by reference in this AD) 

cannot be used for the installation of AOA 

probes having P/N C16291AB. A review of 

airplane maintenance records is acceptable in 

lieu of this inspection if the part number and 

serial number of the installed AOA probes 

can be conclusively determined from that 

review. 

(2) Inspect to determine the part number 

and serial number of each Thales Avionics 

AOA probe, in accordance with paragraph 

3.C.(1)(a) of the Accomplishment Instructions 

of Airbus Service Bulletin A320–34–1452, 

dated January 29, 2010. If any probe is found 

having P/N C16291AB, on which Thales 

Avionics Service Bulletin C16291A–34–009, 

dated September 10, 2009; or Airbus Service 

Bulletin A320–34–1444, dated October 7, 

2009; (which are not incorporated by 

reference in this AD) has been accomplished: 

Within 12 months after the effective date of 

this AD, replace the AOA probe, in 

accordance with a method approved by the 

Manager, International Branch, ANM–116, 

FAA, or European Aviation Safety Agency 

(EASA) (or its delegated agent). A review of 

airplane maintenance records is acceptable in 

lieu of the inspection specified in this 

paragraph if the part number of the installed 

AOA probes can be conclusively determined 

from that review. 

Note 1 to paragraph (g)(2) of this AD: 

Additional guidance for replacing the AOA 

probes may be found in Task 34–11–19–000– 

001–A, Removal of the Angle of Attack 

Sensor, of the Airbus A318/A319/A320/A321 

Aircraft Maintenance Manual, which is not 

incorporated by reference in this AD. 

(h) Exception to the Requirements of 

Paragraph (g) of This AD 

For any airplane on which Airbus 

modification 150006 (installation of Thales 

Avionics AOA probes P/N C16291AB) or 

modification 26934 (installation of Goodrich 

AOA probes P/N 0861ED) has been embodied 

in production, and on which no AOA probe 

replacement has been made since first flight: 

The actions specified in paragraph (g) of this 

AD are not required. 

(i) Parts Installation Limitation and 

Prohibition 

(1) As of the effective date of this AD, no 

person may install a Thales Avionics AOA 

probe, P/N C16291AA, having a serial 

number listed in Thales Avionics Service 

Bulletin C16291A–34–007, Revision 04, 

dated October 11, 2012, on any airplane, 

unless that Thales Avionics probe has been 

inspected, re-identified, and tested, in 

accordance with the Accomplishment 

Instructions of the service information 

specified in paragraphs (i)(1)(i) through 

(i)(1)(iv) of this AD. 

(i) Thales Avionics Service Bulletin 

C16291A–34–007, Revision 04, dated 

October 11, 2012. 

(ii) Thales Avionics Service Bulletin 

C16291A–34–007, Revision 03, dated April 

10, 2012. 

(iii) Thales Avionics Service Bulletin 

C16291A–34–007, Revision 02, dated 

December 16, 2011. 

(iv) Thales Avionics Service Bulletin 

C16291A–34–007, Revision 01, dated 

December 3, 2009. 

(2) As of the effective date of this AD, no 

person may install a Thales Avionics AOA 

probe, P/N C16291AB, on which Thales 

Avionics Service Bulletin C16291A–34–009, 

dated September 10, 2009; or Airbus Service 

Bulletin A320–34–1444, dated October 7, 

2009; (which are not incorporated by 

reference in this AD) has been incorporated. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1405; fax (425) 

227–1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

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. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(k) Related Information 

Refer to MCAI EASA AD 2011–0203, dated 

October 13, 2011, and the service information 

specified in paragraphs (k)(1) through (k)(5) 

of this AD, for related information. 

(1) Airbus Service Bulletin A320–34–1452, 

dated January 29, 2010. 

(2) Thales Avionics Service Bulletin 

C16291A–34–007, Revision 04, dated 

October 11, 2012. 

(3) Thales Avionics Service Bulletin 

C16291A–34–007, Revision 03, dated April 

10, 2012. 

(4) Thales Avionics Service Bulletin 

C16291A–34–007, Revision 02, dated 

December 16, 2011. 

(5) Thales Avionics Service Bulletin 

C16291A–34–007, Revision 01, dated 

December 3, 2009. 

(l) 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) Airbus Service Bulletin A320–34–1452, 

dated January 29, 2010. 


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(ii) Thales Avionics Service Bulletin 

C16291A–34–007, Revision 04, dated 

October 11, 2012. 

(iii) Thales Avionics Service Bulletin 

C16291A–34–007, Revision 03, dated April 

10, 2012. Pages 1, 8, 10, 11, and 13 of this 

document are identified as Revision 03, 

dated April 10, 2012. Pages 2, 7, and 12 are 

identified as Revision 01, dated December 3, 

2009. Page 9 is identified as Revision 02, 

dated December 16, 2011. 

(iv) Thales Avionics Service Bulletin 

C16291A–34–007, Revision 02, dated 

December 16, 2011. Pages 1, and pages 8 

through 10 of this document are identified as 

Revision 02, dated December 16, 2011; pages 

2 through 7, and pages 11 through 13 are 

identified as Revision 01, dated December 3, 

2009. 

(v) Thales Avionics Service Bulletin 

C16291A–34–007, Revision 01, dated 

December 3, 2009. 

(3) For Airbus service information 

identified in this AD, 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.airwortheas@airbus.com; Internet http:// 

www.airbus.com. For Thales Avionics service 

information identified in this AD, contact 

Thales Avionics, Retrofit Manager, 105, 

Avenue du Ge ́ne ́ral Eisenhower, BP 63647, 

31036 Toulouse Cedex 1, France; telephone 

+33 5 61 19 76 95; fax +33 5 61 19 68 20; 

email retrofit.ata@fr.thalesgroup.com; 

Internet http://www.thalesgroup.com/ 

aerospace. 

(4) You may review copies of the 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. 

(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 March 8, 

2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–06172 Filed 3–28–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1346; Directorate 

Identifier 2012–CE–047–AD; Amendment 

39–17401; AD 2013–06–04] 

RIN 2120–AA64 

Airworthiness Directives; REIMS 

AVIATION S.A. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for REIMS 

AVIATION S.A. Model F406 airplanes. 

This AD results from mandatory 

continuing airworthiness information 

(MCAI) issued by an aviation authority 

of another country to identify and 

correct an unsafe condition on an 

aviation product. The MCAI describes 

the unsafe condition as fretting (wear 

and/or chafing) found between the 

elevator pushrod assembly and the 

horizontal tail structure, which could 

cause the elevator pushrod to jam and 

could result in loss of control. We are 

issuing this AD to require actions to 

address the unsafe condition on these 

products. 

DATES: This AD is effective May 3, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of May 3, 2013. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

For service information identified in 

this AD, contact REIMS AVIATION 

INDUSTRIES, Ae ́rodrome de Reims 

Prunay, 51360 Prunay, France; 

telephone: 03.26.48.46.65; fax: 

03.26.49.18.57; Internet: http:// 

www.geciaviation.com/en/. You may 

review copies of the referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. 

FOR FURTHER INFORMATION CONTACT: 

Albert Mercado, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4119; fax: (816) 329–4090; email: 

albert.mercado@faa.gov. 

SUPPLEMENTARY INFORMATION:

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on January 3, 2013 (78 FR 275). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

During maintenance, fretting has been 

found between the elevator pushrod 

assembly and horizontal tail structure on 

Reims F406 aeroplanes. In addition, bending 

was found on a pushrod assembly Part 

Number (P/N) 6015034–1. The investigation 

has not yet established the exact cause(s) of 

these occurrences. 

This condition, if not detected and 

corrected, could lead to failure of a pushrod 

and consequent jamming of the elevator 

controls, possibly resulting in loss of control 

of the aeroplane. 

For the reasons described above, this AD 

requires inspection of the pushrods and 

horizontal tail structure to detect fretting, 

bending or eccentricity and, depending on 

findings, replacement with a serviceable 

pushrod, or repair. This AD also requires the 

return on replaced pushrods to RAI for 

investigation. 

This AD is considered to be an interim 

action and further AD action may follow. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (78 

FR 275, January 3, 2013) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 275, 

January 3, 2013) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 275, 

January 3, 2013). 

Costs of Compliance 

We estimate that this AD will affect 7 

products of U.S. registry. We also 

estimate that it will take about 4 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 


erowe on DSK2VPTVN1PROD with RULES