56818 Federal Register / Vol. 70, No. 188 / Thursday, September 29, 2005 / Rules and Regulations 

TABLE 1.—SERVICE BULLETINS—Continued 

For Airbus Models— Use Airbus Service Bulletin(s)— Revision— Dated—

And, for actions done before the 

effective date of this AD, credit is 

given for prior accomplishing of—

A310–33–2047 ............................. Original ........ April 5, 2004 ........ N/A. 

Modification 

(g) For airplanes on which Airbus 

Modifications 12513 and 12730 have not 

been accomplished: Within 18 months after 

the effective date of this AD, modify the 

electrical power supply logic of the integral 

lighting for the standby horizon indicator in 

the cockpit in accordance with the service 

bulletin. 

Repetitive Operational Tests 

(h) For all airplanes: Within 700 flight 

hours after accomplishing the modification 

required by paragraph (g) of this AD, or 

within 700 flight hours after the effective 

date of this AD, whichever is later, 

accomplish the operational test of the 

integral lighting logic system in accordance 

with the service bulletin. Repeat the test 

thereafter at intervals not to exceed 700 flight 

hours. 

Corrective Action 

(i) If any operational test required by 

paragraph (h) of this AD fails: Before further 

flight, accomplish any applicable repair per 

a method approved by either the Manager, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate; or the 

Direction Ge ́ne ́rale de l’Aviation Civile 

(DGAC) (or its delegated agent). Airbus 

A300–600 and A310 Trouble Shooting 

Manuals; Airbus A300–600 and A310 

Aircraft Wiring Manuals; and Airbus A300–

600 and A310 Aircraft Maintenance Manuals, 

are approved methods for accomplishing the 

repair, as applicable. Except, in the case of 

a failed test in which standard maintenance 

practices do not solve the problem, a repair 

approved by the FAA or the DGAC is 

required. 

Alternative Methods of Compliance 

(AMOCs) 

(j) The Manager, International Branch, 

ANM–116, has the authority to approve 

AMOCs for this AD, if requested in 

accordance with the procedures found in 14 

CFR 39.19. 

Related Information 

(k) French airworthiness directive F–2004–

098, dated July 7, 2004, also addresses the 

subject of this AD. 

Material Incorporated by Reference 

(l) You must use the applicable service 

bulletin identified in Table 2 of this AD to 

perform the actions that are required by this 

AD, unless the AD specifies otherwise. 

TABLE 2.—SERVICE BULLETINS INCORPORATED BY REFERENCE

Airbus Service Bulletin— Revision— Dated—

A300–31–0077 ............................................................................................................................................. 01 ................ January 28, 2005. 

A300–31–6105 ............................................................................................................................................. 03 ................ December 20, 2004. 

A300–33–0126, excluding Appendix 01 ...................................................................................................... Original ........ April 5, 2004. 

A300–33–6049, excluding Appendix 01 ...................................................................................................... 02 ................ April 25, 2005. 

A310–31–2120 ............................................................................................................................................. 03 ................ June 22, 2005. 

A310–33–2047, excluding Appendix 01 ...................................................................................................... Original ........ April 5, 2004. 

The Director of the Federal Register 

approved the incorporation by reference of 

these documents 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 20, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–19229 Filed 9–28–05; 8:45 am] 

BILLING CODE 4910–13–U 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22540; Directorate 

Identifier 2004–NM–137–AD; Amendment 

39–14301; AD 2005–20–08] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–200 and –300 Series Airplanes; 

and Model A340–200 and –300 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Airbus transport category airplanes, 

identified above. This AD requires an 

inspection to determine if a certain 

lower pin (p-pin) of the retraction 

actuator of the main landing gear (MLG) 

is installed. If the affected p-pin is 

installed, this AD requires a one-time 

inspection of the p-pin for correct grease 

hole position and cracking; repetitive 

daily inspections for pin migration; and 

eventual replacement of all p-pins with 

new p-pins. For any p-pin that is 

cracked or shows pin migration, this AD 

requires immediate replacement with a 

new p-pin. Replacing the p-pin with one 

that is correctly manufactured (i.e., that 

has the correct grease hole position) is 

terminating action for the repetitive 

inspections. This AD results from a 

report that a cracked p-pin was found 

when the MLG was removed for 

overhaul. We are issuing this AD to 

prevent failure of the p-pin, which 

could result in degradation of the MLG 

structural integrity and possible 

hazardous landing. 

DATES: Effective October 14, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of October 14, 2005. 

We must receive comments on this 

AD by November 28, 2005. 

Federal Register / Vol. 70, No. 188 / Thursday, September 29, 2005 / Rules and Regulations 56819 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD. 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

room PL–401, Washington, DC 20590. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 

for service information identified in this 

AD. 

You may examine the contents of the 

AD docket on the Internet at http:// 

dms.dot.gov, or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street 

SW., room PL–401, Washington, DC. 

This docket number is FAA–2005–

22540; the directorate identifier for this 

docket 2004–NM–137–AD. 

FOR FURTHER INFORMATION CONTACT: Tim 

Backman, Aerospace Engineer, ANM–

116, International Branch, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2797; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION:

Comments Invited 

Although this is a final rule that was 

not preceded by notice and an 

opportunity for public comment, we 

invite you to submit any relevant 

written data, views, or arguments 

regarding this AD. Include ‘‘Docket No. 

FAA–2005–22540; Directorate Identifier 

2004–NM–137–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the AD. We will consider all 

comments received by the closing date 

and may amend the AD in light of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of that Web site, anyone 

can find and read the comments in any 

of our dockets, including the name of 

the individual who sent the comment 

(or signed the comment on behalf of an 

association, business, labor union, etc.). 

You may review the DOT’s complete 

Privacy Act Statement in the Federal 

Register published on April 11, 2000 

(65 FR 19477–78), or you may visit 

http://dms.dot.gov. 

Examining the Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.gov, or in 

person at the Docket Management 

Facility office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket 

Management Facility office (telephone 

(800) 647–5227) is located on the plaza 

level of the Nassif Building at the DOT 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the Docket 

Management System receives them. 

Discussion 

The Direction Ge ́ne ́rale de l’Aviation 

Civile (DGAC), which is the 

airworthiness authority for France, 

notified us that an unsafe condition may 

exist on Airbus Model A330–200 and 

–300 series airplanes; and Model A340–

200 and –300 series airplanes; equipped 

with main landing gear (MLG) retraction 

actuator lower pin(s) (p-pins) having 

part number (P/N) 201275602. The 

DGAC advises that when the MLG was 

removed for overhaul, a p-pin, which 

connects the lower end of the retraction 

actuator to the main fitting, was found 

to be cracked. Investigators concluded 

that the crack initiated from the center 

grease hole of the p-pin, and that the 

center grease hole was machined in an 

incorrect position, 90 degrees from its 

normal position. The two end holes of 

the p-pin were also found to be 

machined 90 degrees from the original 

design. Failure of the p-pin could lead 

to an undamped extension of the MLG, 

causing high loads throughout the entire 

MLG and damage to the gear structure, 

the side stay assembly, and the bogie 

beam. This condition, if not corrected, 

could result in degradation of the MLG 

structural integrity and a possible 

hazardous landing. 

Relevant Service Information 

Airbus has issued All Operators Telex 

(AOT) A330–32A3181, dated May 27, 

2004 (for Model A330–200, and –300 

series airplanes); and AOT A340–

32A4224, dated May 27, 2004 (for 

Model A340–200 and –300 series 

airplanes). The AOTs describe 

procedures for determining if the 

affected p-pins are installed. For all 

affected p-pins, including spares, the 

AOTs describe procedures for a onetime inspection to determine the 

position of the grease holes and for 

cracking of the p-pin. If the position of 

any grease hole is not correct, the AOTs 

specify that it should be replaced within 

800 flight hours. Until this replacement 

is accomplished, the AOTs give 

procedures for daily external visual 

checks for pin migration. If pin 

migration is found, or if any crack is 

found during the one-time inspection, 

the AOTs specify that the pin should be 

replaced before further flight. The AOTs 

also recommend that operators complete 

a reporting form and send it to the part 

vendor. Accomplishing the actions 

specified in the service information is 

intended to adequately address the 

unsafe condition. The DGAC mandated 

the service information and issued 

French airworthiness directive F–2004–

084, dated June 23, 2004, to ensure the 

continued airworthiness of these 

airplanes in France. 

The AOTs refer to Messier-Dowty 

Service Bulletin A33/34–32–229, 

Revision 1, including Appendixes A 

and B, dated June 4, 2004, as an 

additional source of service information 

for inspecting the p-pins and for 

replacing them with a new pin having 

the same P/N or a new pin having a new 

P/N. 

FAA’s Determination and Requirements 

of This AD 

These airplane models are 

manufactured in France and are type 

certificated for operation in the United 

States under the provisions of section 

21.29 of the Federal Aviation 

Regulations (14 CFR 21.29) and the 

applicable bilateral airworthiness 

agreement. Pursuant to this bilateral 

airworthiness agreement, the DGAC has 

kept the FAA informed of the situation 

described above. We have examined the 

DGAC’s findings, evaluated all pertinent 

information, and determined that we 

need to issue an AD for products of this 

type design that are certificated for 

operation in the United States. 

Therefore, we are issuing this AD to 

prevent failure of the p-pin, which 

could result in degradation of the MLG 

structural integrity and possible 

hazardous landing. This AD requires 

accomplishing the actions specified in 

the service information described 

previously. 

Difference Between This AD and the 

French Airworthiness Directive 

Although the French airworthiness 

directive specifies that operators report 

inspection results to the parts 

manufacturer, this AD does not include 

that requirement. 

56820 Federal Register / Vol. 70, No. 188 / Thursday, September 29, 2005 / Rules and Regulations 

Clarification of Inspection Language 

The French airworthiness directive 

and the AOTs specify that operators 

should do a ‘‘visual inspection’’ or 

‘‘one-time inspection’’ to detect 

incorrectly manufactured p-pins. In this 

AD we refer to this inspection as a 

‘‘detailed inspection.’’ Note 2 of this AD 

defines this inspection. 

The French airworthiness directive 

and the AOTs specify that operators 

should do an ‘‘external visual 

inspection’’ or ‘‘external visual check’’

of the p-pin for pin migration. In this 

AD we refer to this inspection as a 

‘‘general visual inspection.’’ Note 3 of 

this AD defines this inspection. 

Costs of Compliance 

None of the airplanes affected by this 

action are on the U.S. Register. All 

airplanes affected by this AD are 

currently operated by non-U.S. 

operators under foreign registry; 

therefore, they are not directly affected 

by this AD action. However, we 

consider this AD necessary to ensure 

that the unsafe condition is addressed if 

any affected airplane is imported and 

placed on the U.S. Register in the future. 

The following table provides the 

estimated costs to comply with this AD 

for any affected airplane that might be 

imported and placed on the U.S. 

Register in the future. 

ESTIMATED COSTS

Action Work 

hours 

Average labor 

rate per hour Parts cost Cost per airplane 

Inspection to determine P/N of p-pins .......................................................................... 1 $65 None ............ $65 

Detailed inspection for incorrectly manufactured p-pins ............................................... 1 65 None ............ 65 

FAA’s Determination of the Effective 

Date 

No airplane affected by this AD is 

currently on the U.S. Register. 

Therefore, providing notice and 

opportunity for public comment is 

unnecessary before this AD is issued, 

and this AD may be made effective in 

less than 30 days after it is published in 

the Federal Register. 

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 the regulation: 

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 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): 

2005–20–08 Airbus: Amendment 39–14301. 

Docket No. FAA–2005–22540; 

Directorate Identifier 2004–NM–137–AD. 

Effective Date 

(a) This AD becomes effective October 14, 

2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A330–

201, –202, –203, –223, –243, –301, –321, 

–322, –323, –341, –342, and –343 airplanes; 

and Model A340–211, –212, –213, –311, 

–312, and –313 airplanes; certificated in any 

category. 

Unsafe Condition 

(d) This AD results from a report that a ppin, P/N 201275602, which connects the 

lower end of the main landing gear (MLG) 

retraction actuator to the main fitting, was 

found to be cracked when the MLG was 

removed for overhaul. The FAA is issuing 

this AD to prevent failure of the p-pin, which 

could result in degradation of the MLG 

structural integrity and possible hazardous 

landing. 

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. 

Service Information Reference 

(f) For the purposes of this AD, the term 

‘‘AOT’’ (All Operators Telex) means the AOT 

identified in paragraph (f)(1) or (f)(2) of this 

AD, as applicable. 

(1) For Model A330–201, –202, –203, –223, 

–243, –301, –321, –322, –323, –341, –342, 

and –343 airplanes: AOT A330–32A3181, 

dated May 27, 2004. 

(2) For Model A340–211, –212, –213, –311, 

–312, and –313 airplanes: AOT A340–

32A4224, dated May 27, 2004. 

Note 1: The AOTs refer to Messier-Dowty 

Service bulletin A33/34–32–229, Revision 1, 

including Appendixes A and B, dated June 

4, 2004, as an additional source of service 

information for inspecting the p-pins and for 

replacing them with a new pin having the 

same P/N or a new pin having a new P/N. 

Inspection To Determine Part Number 

(g) Within 100 flight cycles or 3 months 

after the effective date of this AD, whichever 

Federal Register / Vol. 70, No. 188 / Thursday, September 29, 2005 / Rules and Regulations 56821 

occurs earlier: Inspect the p-pins of the 

retraction actuator of the MLG to determine 

whether part number (P/N) 201275602 is 

installed. Do the inspection in accordance 

with the applicable AOT. A review of 

airplane maintenance records is acceptable in 

lieu of this inspection if the P/N of the p-pin 

can be conclusively determined from that 

review. If a p-pin with a part number that is 

different than P/N 201275602 is installed, or 

if any P/N 201275602 p-pin has a batch 

number or serial number identified in 

Appendix A of Messier-Dowty Service 

Bulletin A33/34–32–229, Revision 1, dated 

June 4, 2004, no further action is required by 

this AD, except as provided by paragraph (l) 

of this AD. 

Inspection for Cracking and Grease Hole 

Position 

(h) If the inspection required by paragraph 

(g) of this AD shows that an affected P/N 

201275602 is installed, before further flight 

after determining the P/N in accordance with 

paragraph (g) of this AD: Do a detailed 

inspection for cracking of the p-pin and 

position of the grease holes, in accordance 

with the applicable AOT. If any incorrect 

grease hole position is found or if any crack 

is found, do the applicable actions in 

paragraphs (i) and (j) of this AD at the times 

specified in those paragraphs. If all grease 

hole positions are correct and no cracking is 

found, no further action is required by this 

paragraph. 

Note 2: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

Related Investigative and Corrective Actions 

(i) If the inspection required by paragraph 

(h) of this AD shows that a p-pin has any 

incorrect grease hole position, but no 

cracking: Do the actions in paragraph (i)(1) 

and (i)(2) of this AD. Do all actions in 

accordance with the applicable AOT. 

(1) Within 24 hours after the inspection 

required by paragraph (h) of this AD: Do a 

general visual inspection of the p-pin for pin 

migration, in accordance with the applicable 

AOT. Repeat the inspection at intervals not 

to exceed 24 hours until the replacement 

required by paragraph (i)(2) or (j) of this AD 

is accomplished. 

(2) Except as required by paragraph (j) of 

this AD, within 800 flight hours after doing 

the inspection required by paragraph (h) of 

this AD: Replace the p-pin with a new p-pin 

of the same P/N 201275602 with correctly 

positioned grease holes, or with a new p-pin 

having new P/N 201478612, in accordance 

with the applicable AOT. 

Note 3: For the purposes of this AD, a 

general visual inspection is: ‘‘A visual 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made from within touching 

distance unless otherwise specified. A mirror 

may be necessary to ensure visual access to 

all surfaces in the inspection area. This level 

of inspection is made under normally 

available lighting conditions such as 

daylight, hangar lighting, flashlight, or 

droplight and may require removal or 

opening of access panels or doors. Stands, 

ladders, or platforms may be required to gain 

proximity to the area being checked.’’

(j) If any inspection required by paragraphs 

(h) and (i) of this AD shows a crack or pin 

migration, before further flight: Replace the 

p-pin with a new p-pin of the same P/N 

201275602 with correctly positioned grease 

holes, or with a new p-pin having new P/N 

201478612. Do all actions in accordance with 

the applicable AOT. 

No Reporting Required 

(k) Although the AOTs reference a 

reporting requirement in paragraph 4.3, 

‘‘Material—Tooling,’’ that reporting is not 

required by this AD. 

Parts Installation 

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

person may install, on any airplane, a p-pin, 

P/N 201275602, unless it has been inspected 

and any applicable additional inspections 

corrective actions have been done in 

accordance with this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(m)(1) The Manager, 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 § 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 

(n) French airworthiness directive F–2004–

084, dated June 23, 2004, also addresses the 

subject of this AD. 

Material Incorporated by Reference 

(o) You must use Airbus All Operators 

Telex A330–32A3181, dated May 27, 2004; or 

Airbus All Operators Telex A340–32A4224, 

dated May 27, 2004; as applicable; 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 these 

documents 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 20, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–19228 Filed 9–28–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–21170; Directorate 

Identifier 2002–NM–124–AD; Amendment 

39–14298; AD 2005–20–05] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 767–200 and 767–300 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Boeing Model 767–200 and 767–300 

series airplanes. This AD requires 

performing a general visual inspection 

to determine the part number of the Ibeams of the center overhead stowage 

bin modules to identify I-beams having 

9.0g (gravitational acceleration) tie rods 

attached and to determine the 

configuration of the center overhead 

stowage bin modules. For certain center 

overhead stowage bin modules, this AD 

requires installing support straps. This 

AD results from tests conducted by the 

airplane manufacturer. We are issuing 

this AD to prevent failure of the 

attachment of the 9.0g tie rods to the 

center overhead stowage bin modules. 

This failure could result in collapse of 

those stowage bin modules, and 

consequent injury to passengers and 

crew and interference with their ability 

to evacuate the airplane in an 

emergency. 

DATES: Effective November 3, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of November 3, 2005. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street 

SW., Nassif Building, room PL–401, 

Washington, DC. 

Contact Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207, for service 

information identified in this AD.