Federal Register / Vol. 70, No. 196 / Wednesday, October 12, 2005 / Rules and Regulations 59237 

actions will take about 2 work hours per 

airplane, at an average labor rate of $65 

per work hour. Required parts will be 

obtained from operator stores. Based on 

these figures, the estimated cost of the 

AD for U.S. operators is $52,390, or 

$130 per airplane. 

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 have 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 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

(3) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, 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 Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

2005–20–36 Airbus: Amendment 39–14333. 

Docket No. FAA–2005–21862; 

Directorate Identifier 2005–NM–091–AD. 

Effective Date 

(a) This AD becomes effective November 

16, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A320–

111, –211, –212, –214, –231, –232, and –233 

airplanes, and Model A321–111, –112, –131, 

–211, and –231 airplanes, certificated in any 

category; except those airplanes on which 

Airbus Modification 23645 has been 

incorporated in production. 

Unsafe Condition 

(d) This AD was prompted by the results 

of fuel system reviews conducted by the 

manufacturer. We are issuing this AD to 

prevent an ignition source for fuel vapor in 

the wing, which could result in fire or 

explosion in the adjacent wing fuel tank. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Installation of Bonding Lead 

(f) Within 56 months after the effective 

date of this AD, install a bonding lead 

between the low pressure valve and the 

adjacent pipe assembly in each wing, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320–

28–1055, Revision 1, dated March 8, 1994. 

Actions Accomplished Using Original Issue 

of Service Bulletin 

(g) Actions accomplished prior to the 

effective date of this AD in accordance with 

Airbus Service Bulletin A320–28–1055, 

dated July 12, 1993, are considered 

acceptable for compliance with the 

corresponding actions required by paragraph 

(f) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with 14 CFR 39.19 on any 

airplane to which the AMOC applies, notify 

the appropriate principal inspector in the 

FAA Flight Standards Certificate Holding 

District Office. 

Related Information 

(i) French airworthiness directive F–2005–

058, dated April 13, 2005, also addresses the 

subject of this AD. 

Material Incorporated by Reference 

(j) You must use Airbus Service Bulletin 

A320–28–1055, Revision 1, dated March 8, 

1994, to perform the actions that are required 

by this AD, unless the AD specifies 

otherwise. The Director of the Federal 

Register approved the incorporation by 

reference of this document in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, for a 

copy of this service information. You may 

review copies at the Docket Management 

Facility, U.S. Department of Transportation, 

400 Seventh Street SW., room PL–401, Nassif 

Building, Washington, DC; on the Internet at 

http://dms.dot.gov; or at the National 

Archives and Records Administration 

(NARA). For information on the availability 

of this material at the NARA, call (202) 741–

6030, or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on 

September 28, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–20067 Filed 10–11–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–21173; Directorate 

Identifier 2005–CE–22–AD; Amendment 39–

14321; AD 2005–20–25] 

RIN 2120–AA64 

Airworthiness Directives; The Cessna 

Aircraft Company Models 401, 401A, 

401B, 402, 402A, 402B, 402C, 404, 411, 

411A, 414, 414A, 421, 421A, 421B, 

421C, 425, and 441 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA adopts a new 

airworthiness directive (AD) for certain 

The Cessna Aircraft Company (Cessna) 

Models 401, 401A, 401B, 402, 402A, 

402B, 402C, 404, 411, 411A, 414, 414A, 

421, 421A, 421B, 421C, 425, and 441 

airplanes equipped with certain 

avionics bus circuit breaker switches. 

59238 Federal Register / Vol. 70, No. 196 / Wednesday, October 12, 2005 / Rules and Regulations 

This AD requires you to inspect the 

avionics bus circuit breaker switch to 

determine the date code and replace any 

without a date code. This AD also 

imposes a 1,000-hour safe life limit on 

avionics bus circuit breaker switches 

with a date code earlier than 0434. This 

AD results from reports of smoke and a 

burning smell in the cockpit. We are 

issuing this AD to prevent failure of the 

avionics bus circuit breaker switch, 

which could result in smoke and a 

burning smell in the cockpit. This 

failure could lead to reduced ability to 

control the airplane. 

DATES: This AD becomes effective on 

November 9, 2005. 

As of November 9, 2005, the Director 

of the Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulation. 

ADDRESSES: To get the service 

information identified in this AD, 

contact The Cessna Aircraft Company, 

Product Support P.O. Box 7706, 

Wichita, Kansas 67277; telephone: (316) 

517–5800; facsimile: (316) 942–9006. 

To view the AD docket, go to the 

Docket Management Facility; U.S. 

Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

001 or on the Internet at http:// 

dms.dot.gov. The docket number is 

FAA–2005–21173; Directorate Identifier 

2005–CE–22–AD. 

FOR FURTHER INFORMATION CONTACT: 

Gerald Pilj, Aerospace Engineer, FAA, 

Wichita ACO, 1801 Airport Road, MidContinent Airport, Wichita, Kansas 

67209; telephone: (316) 946–4151; 

facsimile: (316) 946–4107. 

SUPPLEMENTARY INFORMATION: 

Discussion 

What events have caused this AD? We 

have received failure reports of certain 

Tyco Electronics circuit breaker 

switches installed on the master 

avionics bus of Cessna Models 401, 

401A, 401B, 402, 402A, 402B, 402C, 

404, 411, 411A, 414, 414A, 421, 421A, 

421B, 421C, 425, and 441 airplanes. 

Failure of these circuit breaker switches 

causes smoke and a burning smell in the 

cockpit. 

Analysis of the circuit breaker switch 

revealed the copper braid inside the 

switch had frayed. Continued use 

causes an internal short. The internal 

short could result in the internal switch 

components or external wiring melting 

because it is no longer protected by the 

circuit breaker. 

The affected circuit breaker switches 

have a date code earlier than 0434 or do 

not have a date code on them. 

The date code consists of four digits. 

The first two represent the year and the 

last two represent the week of the year 

the part was made. 

What is the potential impact if FAA 

took no action? If not prevented, failure 

of the avionics bus circuit breaker 

switch could cause smoke and a burning 

smell in the cockpit. This failure could 

lead to reduced ability to control the 

airplane. 

Has FAA taken any action to this 

point? We issued a proposal to amend 

part 39 of the Federal Aviation 

Regulations (14 CFR part 39) to include 

an AD that would apply to certain 

Cessna Models 401, 401A, 401B, 402, 

402A, 402B, 402C, 404, 411, 411A, 414, 

414A, 421, 421A, 421B, 421C, 425, and 

441 airplanes equipped with certain 

avionics bus circuit breaker switches. 

This proposal was published in the 

Federal Register as a notice of proposed 

rulemaking (NPRM) on June 9, 2005 (70 

FR 33720). The NPRM proposed to 

require you to: 

linspect the avionics bus circuit 

breaker switch to determine the date 

code; 

lreplace all avionics bus circuit 

breaker switches without a date code; 

and 

limplement a 1,000-hour safe life limit 

for all avionics bus circuit breaker 

switches with a date code earlier than 

0434. 

Comments 

Was the public invited to comment? 

We provided the public the opportunity 

to participate in developing this AD. We 

received no comments on the proposal 

or on the determination of the cost to 

the public. 

Conclusion 

What is FAA’s final determination on 

this issue? We have carefully reviewed 

the available data and determined that 

air safety and the public interest require 

adopting the AD as proposed except for 

minor editorial corrections. We have 

determined that these minor 

corrections: 

lare consistent with the intent that was 

proposed in the NPRM for correcting 

the unsafe condition; and 

ldo not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Changes to 14 CFR Part 39—Effect on 

the AD 

How does the revision to 14 CFR part 

39 affect this AD? On July 10, 2002, the 

FAA published a new version of 14 CFR 

part 39 (67 FR 47997, July 22, 2002), 

which governs the FAA’s AD system. 

This regulation now includes material 

that relates to altered products, special 

flight permits, and alternative methods 

of compliance. This material previously 

was included in each individual AD. 

Since this material is included in 14 

CFR part 39, we will not include it in 

future AD actions. 

Costs of Compliance 

How many airplanes does this AD 

impact? We estimate that this AD affects 

7,125 airplanes in the U.S. registry. 

What is the cost impact of this AD on 

owners/operators of the affected 

airplanes? We estimate the following 

costs to accomplish the inspection and 

replacement: 

For Models 401, 401A, 401B, 402, 

402A, 402B, 402C, 404, 411, 411A, 414, 

414A, 421, 421A, 421B, and 421C 

airplanes: 

Labor cost Parts cost Total cost per airplane Total cost on U.S. operators 

4 work hours × $65 an hour = $260. ......... $119 each. $498 (if 2 switches are required). ............. $498 × 6,527 = $3,250,446. 

For Models 425 and 441 airplanes: 

Labor cost Parts cost Total cost per airplane Total cost on U.S. operators 

8 work hours × $65 an hour = $520. ......... $119 each. $758 (if 2 switches are required). ............. $758 × 598 = $453,284. 

Federal Register / Vol. 70, No. 196 / Wednesday, October 12, 2005 / Rules and Regulations 59239 

Authority for This Rulemaking 

What authority does FAA have for 

issuing this rulemaking action? 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 AD. 

Regulatory Findings 

Will this AD impact various entities? 

We have 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. 

Will this AD involve a significant rule 

or regulatory action? 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); and 

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a summary of the costs 

to comply with this AD (and other 

information as included in the 

Regulatory Evaluation) and placed it in 

the AD Docket. You may get a copy of 

this summary by sending a request to us 

at the address listed under ADDRESSES. 

Include ‘‘Docket No. FAA–2005–21173; 

Directorate Identifier 2005–CE–22–AD’’

in your request. 

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 Federal Aviation Administration 

amends part 39 of the Federal Aviation 

Regulations (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. FAA amends § 39.13 by adding a 

new AD to read as follows: 

2005–20–25 The Cessna Aircraft Company: 

Amendment 39–14321; Docket No. 

FAA–2005–21173; Directorate Identifier 

2005–CE–22–AD. 

When Does This AD Become Effective? 

(a) This AD becomes effective on 

November 9, 2005. 

What Other ADs Are Affected By This 

Action? 

(b) None. 

What Airplanes Are Affected by This AD? 

(c) This AD affects the following airplane 

models and serial numbers that are: 

(1) Equipped with an avionics bus circuit 

breaker switch, part number (P/N) CM3589–

50, 593–250–101, 593–250–102, W31–

X2M5A–50, or W31–X1000–50; and 

(2) certificated in any category: 

Model Serial numbers 

401 ... 655 and 401–0001 through 401–0322. 

401A 655 and 401A0001 through 401A0132. 

401B 401B0001 through 401B0221. 

402 ... 402–0001 through 402–0322. 

402A 402A0001 through 402A0129. 

402B 402B0001 through 402B0122, 402B0201 through 402B0249, 402B0301 through 402B0455, 402B0501 through 402B0640, 402B0801 

through 402B0935, 402B1001 through 402B1100, 402B1201 through 402B1250, and 402B1301 through 402B1384. 

402C 689, 402C0001 through 402C0125, 402C0201 through 402C0355, 402C0401 through 402C0528, 402C0601 through 402C0653, 

402C0801 through 402C0807, and 402C0808 through 402C1020. 

404 ... 682, 404–0001 through 404–0136, 404–0201 through 404–0246, 404–0401 through 404–0460, 404–0601 through 404–0695, and 404–

0801 through 404–0859. 

411 ... 642 and 411–0001 through 411–0250. 

411A 411–0251 through 411–0300. 

414 ... 667, 414–0001 through 414–0099, 414–0151 through 414–0175, 414–0251 through 414–0280, 414–0351 through 414–0437, 414–0451 

through 414–0550, 414–0601 through 414–0655, 414–0801 through 414–0855, and 414–0901 through 414–0965. 

414A 414A0001 through 414A0121, 414A0201 through 414A0340, 414A0401 through 414A0535, 414A0601 through 414A0680, 414A0801 

through 414A0858, and 414A1001 through 414A1212. 

421 ... 693 and 421–0001 through 421–0200. 

421A 421A0001 through 421A0158. 

421B 421B0001 through 421B0056, 421B0101 through 421B0147, 421B0201 through 421B0275, 421B0301 through 421B0486, 421B0501 

through 421B0665, and 421B0801 through 421B0970. 

421C 421C0001 through 421C0171, 421C0201 through 421C0350, 421C0401 through 421C0525, 421C0601 through 421C0715, 421C0801 

through 421C0910, 421C1001 through 421C1115, 421C1201 through 421C1257, 421C1401 through 421C1413, and 421C1801 

through 421C1807. 

425 ... 425–0001 through 425–0236. 

441 ... 698 and 441–0001 through 441–0362. 

What is the Unsafe Condition Presented in 

This AD? 

(d) This AD is the result of reports of 

smoke and a burning smell in the cockpit. 

The actions specified in this AD are intended 

to prevent failure of the avionics bus circuit 

breaker switch, which could result in smoke 

and a burning smell in the cockpit. This 

failure could lead to reduced ability to 

control the airplane. 

What Must I do to Address This Problem? 

(e) To address this problem, you must do 

the following: 

59240 Federal Register / Vol. 70, No. 196 / Wednesday, October 12, 2005 / Rules and Regulations 

Actions Compliance Procedures 

(1) Inspect the avionics bus circuit breaker 

switch to determine the part number (P/N) 

and date code. (i) If the P/N is CM3589–50, 

593–250–101, 593–250–102, W31–X2M5A–

50, or W31–X1000–50; and (ii) The date 

code is 0434 or later; then (iii) No further action is required.

Within the next 200 hours time-in-service 

(TIS), the next 12 months, or at the next 

scheduled inspection, after November 9, 

2005 (the effective date of this AD), whichever occurs first.

For Models 425 and 441 airplanes, follow the 

procedures in Cessna Conquest Service 

Bulletin CQB05–2, dated February 21, 

2005, and the applicable maintenance manual. For all other affected airplane models, 

follow the procedures in Cessna Multi-engine Service Bulletin MEB05–1 dated February 21, 2005, and the applicable maintenance manual. 

(2) If the P/N is CM3589–50, 593–250–101, 

593–250–102, W31–X2M5A–50, or W31–

X1000–50 and there is no date code, replace 

the avionics bus circuit breaker switch with a 

P/N CM3589–50 that has a date code of 

0434 or later.

Before further flight after the inspection required in paragraph (e)(1) of this AD.For Models 425 and 441 airplanes, follow the 

procedures in Cessna Conquest Service 

Bulletin CQB05–2, dated February 21, 

2005, and the applicable maintenance manual. For all other affected airplane models, 

follow the procedures in Cessna Multi-engine Service Bulletin MEB05–1, dated February 21, 2005, and the applicable maintenance manual. 

(3) If the P/N is CM3589–50, 593–250–101, 

593–250–102, W31–X2M5A–50, or W31–

X1000–50, or W31–X1000–50 and the date 

code is earlier than 0434, the part has a safe 

life limit of 1,000 hours TIS and must be replaced within the 1,000-hour time limit with a 

P/N CM3589–50 that has a date code of 

0434 or later.

Within the 1,000-hour TIS safe life limit .......... For Models 425 and 441 airplanes, follow the 

procedures in Cessna Conquest Service 

Bulletin CQB05–2, dated February 21, 

2005, and the applicable maintenance manual. For all other affected airplane models, 

follow the procedures in Cessna Multi-engine Service Bulletin MEB05–1, dated February 21, 2005, and the applicable maintenance manual. 

(4) Do not install a P/N CM3589–50, 593–250–

101, 593–250–102, W31–X2M5A–50, or 

W31–X1000–50 that does not have a date 

code or has a date code earlier than 0434.

As of November 9, 2005 (the effective date of 

this AD).

Not applicable. 

May I Request an Alternative Method of 

Compliance? 

(f) You may request a different method of 

compliance or a different compliance time 

for this AD by following the procedures in 14 

CFR 39.19. Unless FAA authorizes otherwise, 

send your request to your principal 

inspector. The principal inspector may add 

comments and will send your request to the 

Manager, Wichita Aircraft Certification Office 

(ACO), FAA. For information on any already 

approved alternative methods of compliance, 

contact Gerald Pilj, Aerospace Engineer, FAA 

Wichita ACO, 1801 Airport Road, MidContinent Airport, Wichita, Kansas 67209; 

telephone: (316) 946–4151; facsimile: (316) 

946–4107. 

Does This AD Incorporate Any Material by 

Reference? 

(g) You must do the actions required by 

this AD following the instructions in Cessna 

Conquest Service Bulletin CQB05–2, dated 

February 21, 2005, and Cessna Multi-engine 

Service Bulletin MEB05–1, dated February 

21, 2005. The Director of the Federal Register 

approved the incorporation by reference of 

this service bulletin in accordance with 5 

U.S.C. 552(a) and 1 CFR part 51. To get a 

copy of this service information, contact The 

Cessna Aircraft Company, Citation Marketing 

Division, Product Support P.O. Box 7706, 

Wichita, Kansas 67277; telephone: (316) 517–

5800; facsimile: (316) 942–9006. To review 

copies of this service information, go to the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html or call (202) 741–6030. To 

view the AD docket, go to the Docket 

Management Facility; U.S. Department of 

Transportation, 400 Seventh Street, SW., 

Nassif Building, Room PL–401, Washington, 

DC 20590–001 or on the Internet at http:// 

dms.dot.gov. The docket number is FAA–

2005–21173; Directorate Identifier 2005–CE–

22–AD. 

Issued in Kansas City, Missouri, on 

September 28, 2005. 

David R. Showers, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–19928 Filed 10–11–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–21464; Directorate 

Identifier 2005–CE–32–AD; Amendment 39–

14320; AD 2005–20–24] 

RIN 2120–AA64 

Airworthiness Directives; SOCATA—

Groupe AEROSPATIALE Model TBM 

700 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA adopts a new 

airworthiness directive (AD) for certain 

SOCATA—Groupe AEROSPATIALE 

(SOCATA) Model TBM 700 airplanes. 

This AD requires you to inspect the 

fuselage skin in the VHF1 antenna 

mounting area for cracks and loose 

rivets. This AD also requires you to 

modify the area if you find cracks or 

loose rivets. This AD results from 

mandatory continuing airworthiness 

information (MCAI) issued by the 

airworthiness authority for France. We 

are issuing this AD to detect and correct 

cracks in the fuselage skin, which could 

result in loss of aircraft pressurization. 

Loss of aircraft pressurization could 

lead to flight crew incapacitation. 

DATES: This AD becomes effective on 

November 9, 2005. 

As of November 9, 2005, the Director 

of the Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulation. 

ADDRESSES: To get the service 

information identified in this AD, 

contact EADS SOCATA Tarbes, 

Direction des Services, 65921 Tarbes 

Cedex 9, France; telephone: 33 (0)5 

62.41.73.00; facsimile: 33 (0)5 

62.41.76.54; or SOCATA AIRCRAFT, 

North Perry Airport, 7501 Pembroke 

Road, Pembroke Pines, Florida 33023. 

To view the AD docket, go to the 

Docket Management Facility; U.S. 

Department of Transportation, 400