54854 Federal Register / Vol. 70, No. 180 / Monday, September 19, 2005 / Proposed Rules 

Parts Installation 

(g) After the effective date of this AD, no 

Messier Bugatti (Labinal) actuator with P/N 

4136290004 or 4136290005 may be installed 

on any airplane. 

No Reporting Required 

(h) Although the service bulletins 

referenced in this AD specify to submit an 

inspection report to the manufacturer, this 

AD does not include that requirement. 

Alternative Methods of Compliance 

(AMOCs) 

(i) The Manager, International Branch, 

ANM–116, FAA, Transport Airplane 

Directorate, has the authority to approve 

AMOCs for this AD, if requested in 

accordance with the procedures found in 14 

CFR 39.19. 

Related Information 

(j) French airworthiness directive F–2005–

038, dated March 2, 2005, also addresses the 

subject of this AD. 

Issued in Renton, Washington, on 

September 9, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–18530 Filed 9–16–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22456; Directorate 

Identifier 2005–NM–128–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A321–100 and –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 A321–100 and 

–200 series airplanes. This proposed AD 

would require replacing the 

crashworthiness pins on the side-stay of 

the main landing gear (MLG) with new 

pins having an increased internal notch 

diameter. This proposed AD results 

from testing on the side-stay 

crashworthiness pins on the MLG, 

which revealed that, in the case of an 

emergency landing, the crashworthiness 

pins installed will not ensure a correct 

MLG collapse. We are proposing this 

AD to prevent a punctured fuel tank, 

which could cause damage to the 

airplane or injury to passengers. 

DATES: We must receive comments on 

this proposed AD by October 19, 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. 

For service information identified in 

this proposed AD, contact Airbus, 1 

Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France. 

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 ‘‘FAA–2005–22456; Directorate 

Identifier 2005–NM–128–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 us that an unsafe condition may 

exist on certain Airbus Model A321–100 

and –200 series airplanes. The DGAC 

advises that, during the development 

qualification program of the 93T 

maximum takeoff weight (MTOW), 

complementary tests performed 

revealed that the main landing gear 

(MLG) side-stay crashworthiness pins 

installed with Airbus Modification 

24982 are not compatible. In the case of 

an emergency landing, the 

crashworthiness pins installed will not 

ensure a correct MLG collapse, and a 

risk of fuel tank puncture that could 

cause damage to the airplane or injury 

to passengers could result. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A320–32–1229, dated August 9, 2001. 

The service bulletin describes 

procedures for replacing the 

crashworthiness pin on the MLG sidestay with a new pin having an increased 

internal notch diameter. 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 2002–074(B) R1, dated March 

20, 2002, to ensure the continued 

airworthiness of these airplanes in 

France. 

The Airbus service bulletin refers to 

Messier-Dowty Service Bulletin 201–

32–26, dated July 20, 2001, as an 

additional source of service information 

for replacing the crashworthiness pins. 

FAA’s Determination and Requirements 

of the Proposed AD 

These airplane models are 

manufactured in France and are type 

Federal Register / Vol. 70, No. 180 / Monday, September 19, 2005 / Proposed Rules 54855 

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 airplanes of this 

type design that are certificated for 

operation in the United States. 

Therefore, we are proposing this AD, 

which would require accomplishing the 

actions specified in the service 

information described previously, 

except as discussed below. 

Difference Between Proposed AD and 

French Airworthiness Directive 

The applicability of the French 

airworthiness directive excludes 

airplanes on which Airbus Service 

Bulletin A320–32–1229 was 

accomplished in service. However, we 

have not excluded those airplanes in the 

applicability of this proposed AD; 

rather, this proposed AD would include 

a requirement to accomplish the actions 

specified in that service bulletin. This 

proposed requirement would ensure 

that the actions specified in the service 

bulletin are accomplished on all 

affected airplanes. Operators must 

continue to operate the airplane in the 

configuration required by this proposed 

AD unless an alternative method of 

compliance is approved. 

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 

Pin replacement ....................................... 2 $65 $0 $130 1 $130 

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–2005–22456; 

Directorate Identifier 2005–NM–128–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by October 19, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A321–

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

A321–211 and –231 airplanes; certificated in 

any category, including airplanes modified in 

production by Airbus Modification 24982, 

but excluding airplanes modified in 

production by Airbus Modification 30046. 

Unsafe Condition 

(d) This AD results from testing on the 

side-stay crashworthiness pins on the main 

landing gear (MLG), which revealed that, in 

the case of an emergency landing, the 

crashworthiness pins installed will not 

ensure a correct MLG collapse. We are 

issuing this AD to prevent a punctured fuel 

tank, which could cause damage to the 

airplane or injury to passengers. 

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. 

Pin Replacement 

(f) Within 27 months after the effective 

date of this AD, replace any crashworthiness 

pin having part number 201525620 with part 

number 201525621, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–32–1229, dated 

August 9, 2001. 

Note 1: Airbus Service Bulletin A320–32–

1229 refers to Messier-Dowty Service 

Bulletin 201–32–26, dated July 20, 2001, as 

an additional source of service information 

for replacing the crashworthiness pins. 

Alternative Methods of Compliance 

(AMOCs) 

(g) 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. 

54856 Federal Register / Vol. 70, No. 180 / Monday, September 19, 2005 / Proposed Rules 

Related Information 

(h) French airworthiness directive 2002–

074(B) R1, dated March 20, 2002, also 

addresses the subject of this AD. 

Issued in Renton, Washington, on 

September 9, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–18529 Filed 9–16–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22454; Directorate 

Identifier 2001–NM–108–AD] 

RIN 2120–AA64 

Airworthiness Directives; Aerospatiale 

Model ATR42–200, ATR42–300, and 

ATR42–320 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 all 

Aerospatiale Model ATR–42–200, ATR 

42–300, and ATR42–320 airplanes. The 

existing AD currently requires 

inspections to determine the proper 

installation of rivets in certain key holes 

and to detect cracks in the area of the 

key holes where rivets are missing; and 

correction of discrepancies. The existing 

AD also requires various inspections of 

the subject area for discrepancies, and 

corrective actions if necessary; and 

replacement of certain cargo door hinges 

with new hinges. For certain airplanes, 

the existing AD also requires 

replacement of friction plates, stop 

fittings, and bolts with new parts. This 

proposed AD would require additional 

corrective actions for certain airplanes. 

This proposed AD is prompted by 

discovery of cracks around key holes on 

certain fuselage frames where rivets 

were missing. We are proposing this AD 

to prevent fatigue cracks of the cargo 

door skin, certain frames, and entry 

door stop fittings and friction plates, 

which could result in reduced structural 

integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by October 19, 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. 

For service information identified in 

this proposed AD, contact Aerospatiale, 

316 Route de Bayonne, 31060 Toulouse, 

Cedex 03, France. 

You can examine the contents of this 

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, on the plaza level of 

the Nassif Building, Washington, DC. 

This docket number is FAA–2005–

22454; the directorate identifier for this 

docket is 2001–NM–108–AD. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–1137; 

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 under 

ADDRESSES. Include ‘‘Docket No. FAA–

2005–22454; Directorate Identifier 

2001–NM–108–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 our docket 

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 can 

review the DOT’s complete Privacy Act 

Statement in the Federal Register 

published on April 11, 2000 (65 FR 

19477–78), or you can visit http:// 

dms.dot.gov. 

Examining the Docket 

You can 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 DMS 

receives them. 

Discussion 

On March 9, 2000, we issued AD 

2000–05–26, amendment 39–11636 (65 

FR 15226, March 22, 2000), for all 

Aerospatiale Model ATR42–200, 

ATR42–300, and ATR42–320 airplanes. 

That AD requires inspections to 

determine the proper installation of 

rivets in certain key holes and to detect 

cracks in the area of the key holes where 

rivets are missing; and correction of 

discrepancies. The existing AD also 

requires various inspections of the 

subject area for discrepancies, and 

corrective actions if necessary; and 

replacement of certain cargo door hinges 

with new hinges. For certain airplanes, 

the existing AD also requires 

replacement of friction plates, stop 

fittings, and bolts with new parts. That 

AD was prompted by discovery of 

cracks around key holes on certain 

fuselage frames where rivets were 

missing. We issued that AD to prevent 

fatigue cracks of the cargo door skin, 

certain frames, and entry door stop 

fittings and friction plates, which could 

result in reduced structural integrity of 

the airplane. 

Actions Since Existing AD Was Issued 

Since we issued AD 2000–05–26, 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 certain 

Aerospatiale Model ATR42–200, 

ATR42–300, and ATR–320 airplanes. 

The DGAC advises that installation of 

Aerospatiale Modification 3184, which 

was mandated in AD 2000–05–26, led to 

a bore over-sizing of the hinge fastener 

holes on certain airplanes. The bore 

over-sizing could lead to reduced