Federal Register / Vol. 70, No. 230 / Thursday, December 1, 2005 / Proposed Rules 72085 

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 supplemental NPRM 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): 

Boeing: Docket No. FAA–2005–20354; 

Directorate Identifier 2004–NM–166–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by December 27, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Boeing Model 

737–100, –200, –200C, –300, –400, and –500 

series airplanes, certificated in any category. 

Unsafe Condition 

(d) This AD results from fuel system 

reviews conducted by the manufacturer. We 

are issuing this AD to prevent chafed wire 

bundles near the center fuel tank, which 

could cause electrical arcing through the tank 

wall and ignition of fuel vapor in the fuel 

tank, and result in a fuel tank explosion. 

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. 

Inspection of Wire Bundles and Fuel Vapor 

Barrier and Corrective Actions 

(f) Within 60 months after the effective 

date of this AD: Do a detailed inspection for 

chafing of the wire bundles located below the 

passenger compartment, above the center fuel 

tank, aft of station 540 to approximately 

station 663.75, right buttock line (RBL) and 

left buttock line (LBL) 24.50; do a detailed 

inspection for damage to the fuel vapor 

barrier area located below the wire bundles, 

as applicable; and do any applicable 

corrective actions; by accomplishing all of 

the applicable actions specified in the 

Accomplishment Instructions of Boeing 

Service Bulletin 737–28–1208, Revision 1, 

dated August 25, 2005. Any corrective 

actions must be done before further flight. 

Note 1: 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.’’

Adjustment/Replacement of Wire Bundle 

Clamps and Installation of Protective Sleeve 

(g) After performing the actions required by 

paragraph (f) of this AD: Before further flight, 

adjust and replace, as applicable, the wire 

bundle clamps located aft of station 540; and 

install a protective sleeve on the upper 

bundle of the bundle run at station 616, RBL 

and LBL 24.50; by accomplishing all of the 

applicable actions specified in the 

Accomplishment Instructions of Boeing 

Service Bulletin 737–28–1208, Revision 1, 

dated August 25, 2005. 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, Seattle Aircraft 

Certification Office, 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. 

Issued in Renton, Washington, on 

November 18, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–23515 Filed 11–30–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–23143; Directorate 

Identifier 2005–NM–177–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A318–100 Series Airplanes, Model 

A319–100 Series Airplanes, Model 

A320–111 Airplanes, Model A320–200 

Series Airplanes, and Model A321–100 

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 

Airbus Model A319, A320, and A321 

series airplanes. The existing AD 

currently requires repetitive inspections 

to detect wear of the inboard flap 

trunnions, and to detect wear or debonding of the protective half-shells; 

corrective actions, if necessary; and 

terminating action. This proposed AD 

would remove the repetitive inspections 

to detect wear of the inboard flap 

trunnions and to detect wear or debonding of the protective half-shells; 

and corrective actions if necessary. This 

proposed AD would add repetitive 

detailed inspections of the inboard flap 

trunnions for any wear marks and of the 

sliding panels for any cracking at the 

long edges, and corrective actions if 

necessary. This proposed AD would 

also add airplanes to the applicability. 

This proposed AD results from reports 

of wear damage to the inboard flap 

trunnions after incorporation of the 

terminating modification. We are 

proposing this AD to detect and correct 

wear of the inboard flap trunnions, 

which could lead to loss of flap surface 

control and consequently result in the 

flap detaching from the airplane. A 

detached flap could result in damage to 

the tail of the airplane. 

DATES: We must receive comments on 

this proposed AD by January 3, 2006. 

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 

72086 Federal Register / Vol. 70, No. 230 / Thursday, December 1, 2005 / Proposed Rules 

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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2125; 

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 ‘‘Docket No. FAA–2005–23143; 

Directorate Identifier 2005–NM–177–

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 

On November 20, 2000, we issued AD 

2000–24–02, amendment 39–12009 (65 

FR 75603, December 4, 2000), for certain 

Airbus Model A319, A320, and A321 

series airplanes. That AD requires 

repetitive inspections to detect wear of 

the inboard flap trunnions, and to detect 

wear or de-bonding of the protective 

half-shells; corrective actions, if 

necessary; and terminating action. That 

AD resulted from issuance of mandatory 

continuing airworthiness information by 

a foreign civil airworthiness authority. 

We issued that AD to prevent chafing 

and resultant wear damage on the 

inboard flap drive trunnions or on the 

protective half-shells, which could 

result in failure of the trunnion primary 

load path; this would adversely affect 

the fatigue life of the secondary load 

path and could lead to loss of the flap. 

Actions Since Existing AD Was Issued 

Since we issued AD 2000–24–02, the 

Direction Generale de l’Aviation Civile 

(DGAC), which is the airworthiness 

authority for France, has notified us that 

operators have reported finding wear 

damage to the inboard flap trunnions 

after incorporating the terminating 

modification of AD 2000–24–02. Wear is 

caused when the sliding panel hook 

moves out of the protected area of the 

trunnion during flap operation. Wear of 

the inboard flap trunnion associated 

with a drive failure at track 2 or 

associated with a hard jam at track 1 

could lead to loss of flap surface control. 

A free moveable flap could result in the 

flap detaching from the airplane. A 

detached flap could result in damage to 

the tail of the airplane. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A320–57–1133, dated July 28, 2005. The 

service bulletin describes procedures for 

doing repetitive detailed inspections of 

the inboard flap trunnions for any wear 

marks and of the sliding panels for any 

cracking at the long edges, doing any 

corrective actions if necessary, and 

reporting inspection results to the 

manufacturer. The corrective actions 

include the following: 

• If the sliding panel is damaged, 

replacing the sliding panel with a new 

sliding panel at the next opportunity. 

• If the trunnion is damaged, 

reworking the trunnion to a smooth 

contour and measuring the maximum 

depth of rework. 

• If the maximum allowed damage 

limit of the trunnion has been exceeded, 

replacing the trunnion or flap before 

further flight. 

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–2005–139, 

dated August 3, 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 AD 

action is necessary for airplanes of this 

type design that are certificated for 

operation in the United States. 

This proposed AD would supersede 

AD 2000–24–02 and would only 

continue to require accomplishing the 

modification (the terminating action of 

AD 2000–24–02). This proposed AD 

would also require repetitive detailed 

inspections of the inboard flap 

trunnions for any wear marks and of the 

sliding panels for any cracking at the 

long edges, and corrective actions if 

necessary. 

Clarification of Applicability 

French airworthiness directive F–

2005–139 is applicable to Airbus Model 

A318, A319, A320, and A321 airplanes, 

all serial numbers that have received 

Airbus modification 26495 in 

production or Airbus Service Bulletin 

A320–27–1117 in service. In this NPRM, 

however, we have excluded reference to 

Model A318–100 series airplanes that 

have accomplished Airbus Service 

Bulletin A320–27–1117 in service from 

the applicability, since that service 

bulletin does not apply to those 

airplanes. Also, this NPRM applies to all 

Model A319–100 series airplanes, 

Model A320–111 airplanes, Model 

A320–200 series airplanes, and Model 

A321–100 series airplanes. For all of 

these airplanes, either Airbus 

modification 26495 was accomplished 

in production or Airbus Service Bulletin 

A320–27–1117 was accomplished in 

Federal Register / Vol. 70, No. 230 / Thursday, December 1, 2005 / Proposed Rules 72087 

service (as required by AD 2000–24–02 

or French airworthiness directive 1996–

271–092(B) R3, dated August 11, 1999). 

Therefore, for Model A319–100 series 

airplanes, Model A320–111 airplanes, 

Model A320–200 series airplanes, and 

Model A321–100 series airplanes, it is 

not necessary to reference Airbus 

modification 26495 or Airbus Service 

Bulletin A320–27–1117 in the 

applicability of the NPRM. 

Clarification of Compliance Times for 

Corrective Actions 

Where Airbus Service Bulletin A320–

57–1133 specifies replacing the sliding 

panel at the next opportunity, this 

proposed AD would require replacing it 

within 600 flight hours after the 

proposed inspection. 

If the trunnion is found damaged 

during any inspection, the service 

bulletin does not specify a compliance 

time for reworking the trunnion and 

measuring the maximum rework depth. 

This proposed AD would require those 

corrective actions before further flight 

after the proposed inspection. 

Where the service bulletin specifies 

contacting the manufacturer for a grace 

period assessment after replacing the 

trunnion or flap, this proposed AD 

would instead require contacting the 

FAA or DGAC for the grace period 

assessment. 

Clarification of Inspection Terminology 

‘‘Visually examine’’ as specified in 

Airbus Service Bulletin A320–57–1133 

is referred to as a ‘‘detailed inspection’’

in this proposed AD. We have included 

the definition for a detailed inspection 

in a note in the proposed AD. 

Clarification of Alternative Method of 

Compliance (AMOC) Paragraph 

We have revised this action to clarify 

the appropriate procedure for notifying 

the principal inspector before using any 

approved AMOC on any airplane to 

which the AMOC applies. 

Change to Existing AD 

This proposed AD would retain 

certain requirements of AD 2000–24–02. 

Since AD 2000–24–02 was issued, the 

AD format has been revised, and certain 

paragraphs have been rearranged. Also, 

the requirements in paragraphs (a) 

through (e) of AD 2000–24–02 have not 

been retained in this proposed AD. As 

a result, the requirement in paragraph (f) 

of AD 2000–24–02 corresponds to the 

requirement of paragraph (f) in this 

proposed 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 

Terminating modification (required by AD 2000–24–02).14 $65 Provided by manufacturer.$910 ....................... 719 $654,290. 

Detailed inspection (new proposed action).2 65 None ...................... $130, per inspection cycle.719 $93,470, per inspection 

cycle. 

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 removing amendment 39–12009 (65 

FR 75603, December 4, 2000) and 

adding the following new airworthiness 

directive (AD): 

Airbus: Docket No. FAA–2005–23143; 

Directorate Identifier 2005–NM–177–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by January 3, 2006. 

Affected ADs 

(b) This AD supersedes AD 2000–24–02. 

Applicability 

(c) This AD applies to the airplanes 

identified in paragraphs (c)(1) and (c)(2) of 

this AD, certificated in any category. 

(1) Airbus Model A318–111 and –112 

airplanes on which Airbus Modification 

26495 has been incorporated in production. 

(2) All Airbus Model A319–111, –112, 

–113, –114, –115, –131, –132, and –133 

airplanes; Model A320–111 airplanes; Model 

72088 Federal Register / Vol. 70, No. 230 / Thursday, December 1, 2005 / Proposed Rules 

A320–211, –212, –214, –231, –232, and –233 

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

–131 airplanes. 

Unsafe Condition 

(d) This AD results from reports of wear 

damage to the inboard flap trunnions after 

incorporation of the terminating 

modification. We are issuing this AD to 

detect and correct wear of the inboard flap 

trunnions, which could lead to loss of flap 

surface control and consequently result in 

the flap detaching from the airplane. A 

detached flap could result in damage to the 

tail of the airplane. 

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. 

Restatement of Certain Requirements of AD 

2000–24–02 

Modification 

(f) For Model A319–111, –112, –113, –114, 

–115, –131, –132, and –133 airplanes; Model 

A320–111 airplanes; Model A320–211, –212, 

–214, –231, –232, and –233 airplanes; and 

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

except those on which Airbus Modification 

26495 has been accomplished in production: 

Within 18 months after January 8, 2001 (the 

effective date of AD 2000–24–02), modify the 

sliding panel driving mechanism of the flap 

drive trunnions, in accordance with Airbus 

Service Bulletin A320–27–1117, Revision 02, 

dated January 18, 2000. 

Note 1: Accomplishment of the 

modification required by paragraph (f) of this 

AD before January 8, 2001, in accordance 

with Airbus Service Bulletin A320–27–1117, 

dated July 31, 1997; or Revision 01, dated 

June 25, 1999, is acceptable for compliance 

with that paragraph. 

Requirements of this AD 

Detailed Inspections 

(g) For all airplanes: At the latest of the 

applicable compliance times specified in 

paragraphs (g)(1), (g)(2), and (g)(3) of this AD, 

do a detailed inspection of the inboard flap 

trunnions for any wear marks and of the 

sliding panels for any cracking at the long 

edges, and do any corrective actions as 

applicable, by accomplishing all of the 

applicable actions specified in the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1133, dated July 

28, 2005; except as provided by paragraph (h) 

of this AD. Any corrective actions must be 

done at the compliance times specified in 

Figures 5 and 6, as applicable, of the service 

bulletin; except as provided by paragraph (i) 

of this AD. Repeat the detailed inspections 

thereafter at intervals not to exceed 4,000 

flight hours. 

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.’’

(1) Before accumulating 4,000 total flight 

hours on the inboard flap trunnion since 

new. 

(2) Within 4,000 flight hours after 

accomplishing paragraph (f) of this AD. 

(3) Within 600 flight hours after the 

effective date of this AD. 

No Reporting Requirement 

(h) Although Airbus Service Bulletin 

A320–57–1133, dated July 28, 2005, specifies 

to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

Compliance Times 

(i) Where Airbus Service Bulletin A320–

57–1133, dated July 28, 2005, specifies 

replacing the sliding panel at the next 

opportunity, replace it within 600 flight 

hours after the inspection required by 

paragraph (g) of this AD. If the trunnion is 

found damaged during any inspection 

required by paragraph (g) of this AD, do the 

corrective actions specified in the service 

bulletin before further flight. Where the 

service bulletin specifies contacting the 

manufacturer for a grace period assessment 

after replacing the trunnion or flap, contact 

the FAA or Direction Ge ́ne ́rale de l′Aviation 

Civile (DGAC) for the grace period 

assessment. 

Alternative Methods of Compliance (AMOCs) 

(j)(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 

(k) French airworthiness directive F–2005–

139, dated August 3, 2005, also addresses the 

subject of this AD. 

Issued in Renton, Washington, on 

November 18, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–23514 Filed 11–30–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–23142; Directorate 

Identifier 2005–NM–154–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A319–131, –132, and –133; A320–232 

and –233; and A321–131 and –231 

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 A319–131, –132, 

and –133; A320–232 and –233; and 

A321–131 and –231 airplanes. This 

proposed AD would require inspecting 

for cracks or failure of the primary load 

path components of the engine forward 

mount, and corrective action if 

necessary. This proposed AD also 

would require removing, re-installing, 

and re-torquing the attachment bolts for 

the secondary load path. This proposed 

AD results from a report that, during 

modification of certain engine forward 

mount assemblies of the left and right 

engines done at an engine shop visit, an 

incorrect torque was applied to the 

attachment bolts. We are proposing this 

AD to prevent structural failure of the 

secondary load path of the forward 

engine mount, which, if combined with 

failure of the primary load path, could 

result in separation of the engine from 

the airplane. 

DATES: We must receive comments on 

this proposed AD by January 3, 2006. 

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.