Federal Register / Vol. 70, No. 186 / Tuesday, September 27, 2005 / Proposed Rules 56381 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22528; Directorate 

Identifier 2005–NM–125–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A318–100 and A319–100 Series 

Airplanes; A320–111 Airplanes; A320–

200 Series Airplanes; and A321–100 

and A321–200 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain Airbus Model A318–100 and 

A319–100 series airplanes; A320–111 

airplanes; A320–200 series airplanes; 

and A321–100 and A321–200 series 

airplanes. This proposed AD would 

require a one-time inspection of the 

horizontal hinge pin of the 103VU 

electrical panel in the avionics 

compartment to determine if the hinge 

pin can move out of the hinge, and 

related investigative and corrective 

actions if necessary. This proposed AD 

results from a report indicating that 

electrical wire damage was found in the 

103VU electrical panel due to contact 

between the hinge pin and the adjacent 

electrical wire harness. We are 

proposing this AD to prevent contact 

between the horizontal hinge pin and 

the adjacent electrical wire harness, 

which could result in damage to 

electrical wires, and consequent arcing 

and/or failure of associated systems. 

DATES: We must receive comments on 

this proposed AD by October 27, 2005. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed 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 

proposed AD. 

FOR FURTHER INFORMATION CONTACT: Tim 

Dulin, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2141; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to submit any relevant 

written data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed in the 

ADDRESSES section. Include the docket 

number ‘‘FAA–2005–22528; Directorate 

Identifier 2005–NM–125–AD’’ at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the proposed AD. We will consider all 

comments received by the closing date 

and may amend the proposed 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 proposed 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 the FAA that an unsafe 

condition may exist on certain Airbus 

Model A318–100 and A319–100 series 

airplanes; A320–111 airplanes; A320–

200 series airplanes; and A321–100 and 

A321–200 series airplanes. The DGAC 

advises that electrical wire damage was 

found in the 103VU electrical panel, 

which is located in the avionics 

compartment. Investigation revealed 

contact between the horizontal hinge 

pin and an adjacent electrical wire 

harness, due to migration of the hinge 

pin. This condition, if not corrected, 

could result in damage to electrical 

wires, and consequent arcing and/or 

failure of associated systems. 

Relevant Service Information 

Airbus has issued All Operators Telex 

(AOT) 25A1440, dated February 15, 

2005. The AOT describes procedures for 

inspecting the 103VU electrical panel 

horizontal hinge pin to determine if the 

pin can move out of the hinge. If there 

is no hinge movement, the AOT states 

that no further action is required. If 

there is movement, the AOT states that 

operators should do the related 

investigative action of inspecting for 

damage to the adjacent electrical 

harness, and do all necessary corrective 

actions. The corrective actions include 

reworking the hinge, and repairing any 

damage to the electrical harness. 

Accomplishing the actions specified in 

the service information is intended to 

adequately address the unsafe 

condition. The DGAC mandated the 

AOT and issued French airworthiness 

directive F–2005–052 R1, dated April 

13, 2005, to ensure the continued 

airworthiness of these airplanes in 

France. 

FAA’s Determination and Requirements 

of the Proposed 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 

require accomplishing the actions 

specified in the service information 

described previously. 

56382 Federal Register / Vol. 70, No. 186 / Tuesday, September 27, 2005 / Proposed Rules 

Clarification of Inspection Language 

The service bulletin and the French 

airworthiness directive request that 

operators ‘‘inspect’’ for hinge pin 

movement. This proposed AD defines 

that inspection as a ‘‘general visual 

inspection.’’ This inspection is defined 

in Note 1 of this AD. 

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators to 

comply with this proposed AD. 

ESTIMATED COSTS

Action Work hours 

Average 

labor rate 

per hour 

Parts Cost per 

airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Inspection .............................................................................. 1 $65 None .... $65 696 $45,240 

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 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 proposed 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 proposed 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, Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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): 

Airbus: Docket No. FAA–2005–22528; 

Directorate Identifier 2005–NM–125–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by October 27, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A318–

111 and –112; A319–111, –112, –113, –114, 

–115, –131, –132, and –133; A320–111, –211, 

–212, –214, –231, –232, and –233; and A321–

111, –112, –131, –211 and –231 airplanes; 

certificated in any category; serial numbers 

(S/Ns) 1 through 2396 inclusive, except S/Ns 

2104, 2143, 2248, 2270, 2347, 2366, 2372, 

2376, 2384, 2386, 2388, 2390, 2391, 2393, 

and 2395. 

Unsafe Condition 

(d) This AD results from a report indicating 

that electrical wire damage was found in the 

103VU electrical panel due to contact 

between the hinge pin and the adjacent 

electrical wire harness. The FAA is issuing 

this AD to prevent contact between the 

horizontal hinge pin and the adjacent 

electrical wire harness, which could result in 

damage to electrical wires, and consequent 

arcing and/or failure of associated systems. 

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. 

Inspections and Corrective Actions 

(f) Within 600 flight hours after the 

effective date of this AD, do a general visual 

inspection of the horizontal hinge pin of the 

103VU electrical panel in the avionics 

compartment to determine if the pin can 

move out of the hinge, and do any applicable 

related investigative and corrective actions, 

including repair of any damaged electrical 

wires, before further flight. Do all the actions 

in accordance with Airbus All Operators 

Telex 25A1440, dated February 15, 2005. 

Note 1: 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.’’

No Reporting 

(g) Although All Operators Telex 25A1440, 

dated February 15, 2005, specifies that 

operators should send the results of 

inspections to the manufacturer, that action 

is not required by 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 § 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–

052 R1, dated April 13, 2005, also addresses 

the subject of this AD. 

Federal Register / Vol. 70, No. 186 / Tuesday, September 27, 2005 / Proposed Rules 56383 

Issued in Renton, Washington, on 

September 16, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–19232 Filed 9–26–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22529; Directorate 

Identifier 2005–NM–099–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 767–200, –300, and –300F Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) that applies to certain 

Boeing Model 767–200, –300, and 

–300F series airplanes. The existing AD 

currently requires repetitive inspections 

of the lubrication passage and link 

assembly joint in the inboard and 

outboard flaps of the trailing edge for 

discrepancies, and corrective action if 

necessary. This proposed AD would 

require new inspections for cracking or 

severe wear of the bearings of the link 

assembly, and corrective actions if 

necessary. This proposed AD would 

also require inspecting any link 

assembly not previously inspected for 

damage and replacing it with a new 

assembly if necessary. This proposed 

AD also ends the existing repetitive 

inspections for certain airplanes, and 

extends the repetitive interval for the 

existing repetitive inspections and the 

compliance time for the corrective 

action on certain other airplanes. This 

proposed AD also provides an optional 

terminating action that would end the 

repetitive inspections. This proposed 

AD results from additional reports 

indicating fractured bearings of the link 

assembly joint in the inboard and 

outboard flaps of the trailing edge. We 

are proposing this AD to prevent failure 

of the bearings in the link assembly 

joint, which could result in separation 

of the inboard or outboard flap and 

consequent loss of control of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by November 14, 

2005. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed 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 Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207, for service 

information identified in this proposed 

AD. 

FOR FURTHER INFORMATION CONTACT: 

Candice Gerretsen, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6428; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to submit any relevant 

written data, views, or arguments 

regarding this proposed AD. Include the 

docket number ‘‘Docket No. FAA–2005–

22529; Directorate Identifier 2005–NM–

099–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the proposed AD. We will 

consider all comments received by the 

closing date and may amend the 

proposed 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 proposed 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 may can 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 

On January 16, 2002, we issued AD 

2002–01–15, amendment 39–12609 (67 

FR 4328, January 30, 2002), for certain 

Boeing Model 767–200, –300, and 

–300F series airplanes. That AD requires 

repetitive inspections of the lubrication 

passage and link assembly joint in the 

inboard and outboard flaps of the 

trailing edge for discrepancies, and 

corrective action if necessary. That AD 

resulted from reports of fractured 

bearings and blocked lubrication 

passages of the link assembly joint in 

the inboard and outboard flaps of the 

trailing edge. We issued that AD to 

prevent failure of the bearings in the 

link assembly joint, which could result 

in separation of the outboard flap and 

consequent loss of control of the 

airplane. 

Actions Since Existing AD Was Issued 

The preamble to AD 2002–01–15 

explains that we consider the 

requirements ‘‘interim action’’ and were 

considering further rulemaking. We now 

have determined that further 

rulemaking is indeed necessary, and 

this proposed AD follows from that 

determination. 

Since we issued AD 2002–01–15, we 

have received reports of numerous 

additional incidents of fractured 

bearings of the link assembly joint in the 

inboard and outboard flaps of the 

trailing edge. In several of these 

additional incidents, the bearings were 

properly lubricated. Metallurgical 

examination of fractured bearings 

indicated environmentally assisted 

cracking. 

These additional incidents support 

the data referenced in the 

SUPPLEMENTARY INFORMATION section of 

AD 2002–01–15 that indicate that 

bearings of the link assembly joint may 

fail even when they are properly 

lubricated. However, paragraph (b)(1) of