Federal Register / Vol. 70, No. 162 / Tuesday, August 23, 2005 / Proposed Rules 49213

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22170; Directorate 

Identifier 2005–NM–073–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A320–111, –211, –212, 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 A320–111, –211, 

–212, and –231 airplanes. This proposed 

AD would require, for certain airplanes, 

modifying the cables and access holes to 

the inner tank fuel pumps; and, for 

certain other airplanes, inspecting the 

fuel pump access holes and modifying 

the access holes, if necessary. This 

proposed AD results from fuel system 

reviews conducted by the manufacturer. 

We are proposing this AD to prevent 

chafing of the fuel pump cables, which 

could result in electrical arcing and 

possible ignition of fuel vapors and 

consequent explosion of the fuel tank.

DATES: We must receive comments on 

this proposed AD by September 22, 

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. Include the 

docket number ‘‘Docket No. FAA–2005–

22170; Directorate Identifier 2005–NM–

073–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 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 FAA has examined the 

underlying safety issues involved in 

recent fuel tank explosions on several 

large transport airplanes, including the 

adequacy of existing regulations, the 

service history of airplanes subject to 

those regulations, and existing 

maintenance practices for fuel tank 

systems. As a result of those findings, 

we issued a regulation titled ‘‘Transport 

Airplane Fuel Tank System Design 

Review, Flammability Reduction and 

Maintenance and Inspection 

Requirements’’ (67 FR 23086, May 7, 

2001). In addition to new airworthiness 

standards for transport airplanes and 

new maintenance requirements, this 

rule included Special Federal Aviation 

Regulation No. 88 (‘‘SFAR 88,’’

Amendment 21–78, and subsequent 

Amendments 21–82 and 21–83). 

Among other actions, SFAR 88 

requires certain type design (i.e., type 

certificate (TC) and supplemental type 

certificate (STC)) holders to substantiate 

that their fuel tank systems can prevent 

ignition sources in the fuel tanks. This 

requirement applies to type design 

holders for large turbine-powered 

transport airplanes and for subsequent 

modifications to those airplanes. It 

requires them to perform design reviews 

and to develop design changes and 

maintenance procedures if their designs 

do not meet the new fuel tank safety 

standards. As explained in the preamble 

to the rule, we intended to adopt 

airworthiness directives to mandate any 

changes found necessary to address 

unsafe conditions identified as a result 

of these reviews. 

In evaluating these design reviews, we 

have established four criteria intended 

to define the unsafe conditions 

associated with fuel tank systems that 

require corrective actions. The 

percentage of operating time during 

which fuel tanks are exposed to 

flammable conditions is one of these 

criteria. The other three criteria address 

the failure types under evaluation: 

Single failures, single failures in 

combination with another latent 

condition(s), and in-service failure 

experience. For all four criteria, the 

evaluations included consideration of 

previous actions taken that may mitigate 

the need for further action. 

The Joint Aviation Authorities (JAA) 

has issued a regulation that is similar to 

SFAR 88. (The JAA is an associated 

body of the European Civil Aviation 

Conference (ECAC) representing the 

civil aviation regulatory authorities of a 

number of European States who have 

agreed to co-operate in developing and 

implementing common safety regulatory 

standards and procedures.) Under this 

regulation, the JAA stated that all 

members of the ECAC that hold type 

certificates for transport category 

airplanes are required to conduct a 

design review against explosion risks. 

We have determined that the actions 

identified in this AD are necessary to 

reduce the potential of ignition sources 

inside fuel tanks, which, in combination 

with flammable fuel vapors, could result 

in fuel tank explosions and consequent 

loss of the airplane. 

49214 Federal Register / Vol. 70, No. 162 / Tuesday, August 23, 2005 / Proposed Rules 

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 A320–

111, –211, –212, and –231 airplanes. 

The DGAC advises that a design review 

of the electrical cables and structure 

around the access holes to the inner 

tank fuel pumps revealed that cables 

could be damaged by chafing against 

sharp edges of the fuel pump access 

holes. This condition, if not prevented, 

could result in electrical arcing and 

possible ignition of fuel vapors and 

consequent explosion of the fuel tank.

Relevant Service Information 

Airbus has issued, for certain Model 

A320–111, –211, and –231 airplanes, 

Service Bulletin A320–28–1008, 

Revision 1, dated April 10, 1989, which 

describes procedures for modifying the 

cables and access holes to the inner tank 

fuel pumps. The modification includes 

chamfering the edges of the fuel pump 

access holes, applying protective 

material to the chamfered areas, 

installing backshells to the cable 

connectors, and securing the cables to 

the backshells. 

Airbus has also issued, for certain 

Model A320–211, –212, and –231 

airplanes, Service Bulletin A320–28–

1054, dated August 23, 1993, which 

describes procedures for performing a 

visual inspection for correct radius of 

the fuel pump access holes and, as 

applicable, modifying the fuel pump 

access holes. The modification includes 

chamfering the edges of all access holes 

to the inner tank fuel pumps and 

applying protective material to the 

chamfered areas. The service bulletin 

also describes procedures for reporting 

all findings to Airbus. 

Accomplishing the actions specified 

in the service information is intended to 

adequately address the unsafe 

condition. 

The DGAC mandated accomplishment 

of the service bulletins and issued 

French airworthiness directive F–2005–

031, dated February 16, 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 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 under ‘‘Difference 

Between Service Information and the 

Proposed AD.’’

Difference Between French 

Airworthiness Directive and the 

Proposed AD 

The applicability of French 

airworthiness directive F–2005–031 

excludes airplanes that accomplished 

Airbus Service Bulletin A320–28–1008, 

Revision 1, in service and airplanes that 

accomplished Airbus Service Bulletin 

A320–28–1054 in service. However, we 

have not excluded those airplanes from 

the applicability of this proposed AD; 

rather, this proposed AD includes a 

requirement to accomplish the actions 

specified in those service bulletins. This 

requirement would ensure that the 

actions specified in the service bulletins 

and required by this proposed AD 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. 

Difference Between Service Information 

and the Proposed AD 

Although Airbus Service Bulletin 

A320–28–1054 describes procedures for 

reporting all findings to Airbus, this 

proposed AD would not require this 

report. The FAA does not need this 

information from operators. 

Clarification of Inspection Terminology 

While Airbus Service Bulletin A320–

28–1054 specifies a ‘‘visual inspection,’’

this proposed AD would require a 

‘‘general visual inspection’’ to avoid any 

confusion about the proper type of 

inspection. We have included a 

definition of this type of inspection in 

the proposed AD. 

Costs of Compliance 

This proposed AD would affect about 

17 airplanes of U.S. registry. The 

proposed actions would be performed at 

an average labor rate of $65 per work 

hour, and any needed parts would be 

supplied from operator inventory. 

For about 7 U.S.-registered airplanes 

subject to Airbus Service Bulletin 

A320–28–1008, Revision 1, dated April 

10, 1989, the proposed modification 

would take about 3 work hours. Based 

on these figures, the estimated cost of 

this proposed modification for U.S. 

operators is $1,365, or $195 per 

airplane. 

For about 10 U.S.-registered airplanes 

subject to Airbus Service Bulletin 

A320–28–1054, dated August 23, 1993, 

the proposed inspection would take 

about 1 work hour. Based on these 

figures, the estimated cost of this 

proposed inspection for U.S. operators 

is $650, or $65 per airplane. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in subtitle VII, 

part A, subpart III, section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this 

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. See the ADDRESSES

section for a location to examine the 

regulatory evaluation.

Federal Register / Vol. 70, No. 162 / Tuesday, August 23, 2005 / Proposed Rules 49215

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–2005–22170; 

Directorate Identifier 2005–NM–073–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by September 22, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A320–

111, –211, –212, and –231 airplanes, 

certificated in any category, that have not 

received Airbus Modification 21088 or 21999 

in production; and airplanes that have 

received Airbus Modification 21088 in 

production and have manufacturer’s serial 

number 91 to 113 inclusive and 140 to 189 

inclusive. 

Unsafe Condition 

(d) This AD results from fuel systems 

reviews conducted by the manufacturer. We 

are issuing this AD to prevent chafing of the 

fuel pump cables, which could result in 

electrical arcing and possible ignition of fuel 

vapors and consequent explosion of the fuel 

tank. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Inspection and Modification of Fuel Pump 

Access Holes 

(f) Within 58 months after the effective 

date of this AD, perform the actions required 

by paragraph (f)(1) or (f)(2) of this AD, as 

applicable. 

(1) For airplanes that have not received 

Airbus Modification 21088 or 21999 in 

production: Modify the cables and access 

holes to the inner tank fuel pumps, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320–

28–1008, Revision 1, dated April 10, 1989. 

(2) For airplanes that have received Airbus 

Modification 21088 in production and have 

manufacturer’s serial number 91 to 113 

inclusive and 140 to 189 inclusive: Perform 

a general visual inspection for the correct 

radius of the fuel pump access holes and 

modify the access holes, if necessary, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320–

28–1054, dated August 23, 1993. Do any 

applicable repairs before further flight.

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 Requirement 

(g) Although Airbus Service Bulletin 

A320–28–1054, dated August 23, 1993, 

describes procedures for reporting inspection 

findings to Airbus, this AD does not require 

such a report. 

Alternative Methods of Compliance 

(AMOCs) 

(h) 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. 

Related Information 

(i) French airworthiness directive F–2005–

031, dated February 16, 2005, also addresses 

the subject of this AD.

Issued in Renton, Washington, on August 

11, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 05–16753 Filed 8–22–05; 8:45 am] 

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2000–NE–42–AD] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company CF34 Series 

Turbofan Engines

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) for General Electric 

Company (GE) CF34–1A, –3A, –3A1, 

–3A2, –3B, and –3B1 turbofan engines. 

That AD currently requires a onetime 

inspection, and if necessary replacing 

certain fan disks for electrical arc-out 

indications. That AD also reduces the 

life limit of certain fan disks. This 

proposed AD would require the same 

actions and adds one disk part number 

(P/N) and serial number (SN) to the 

affected fan disks. This proposed AD 

results from an error in the first part 

number and serial number listed in 

Table 1 of the original AD. We are 

proposing this AD to prevent rupture of 

the fan disk due to cracks that initiate 

at an electrical arc-out, which could 

result in an uncontained failure of the 

engine.

DATES: We must receive any comments 

on this proposed AD by October 24, 

2005.

ADDRESSES: Use one of the following 

addresses to comment on this proposed 

AD: 

• By mail: Federal Aviation 

Administration (FAA), New England 

Region, Office of the Regional Counsel, 

Attention: Rules Docket No. 2000–NE–

42–AD, 12 New England Executive Park, 

Burlington, MA 01803–5299. 

• By fax: (781) 238–7055. 

• By e-mail: 9-aneadcomment@faa.gov. 

You can get the service information 

identified in this proposed AD from GE 

Aircraft Engines, 1000 Western Avenue, 

Lynn, MA 01910; Attention: CF34 

Product Support Engineering, Mail 

Zone: 34017; telephone (781) 594–6323; 

fax (781) 594–0600. 

You may examine the AD docket at 

the FAA, New England Region, Office of 

the Regional Counsel, 12 New England 

Executive Park, Burlington, MA.

FOR FURTHER INFORMATION CONTACT:

Eugene Triozzi, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803–5299; telephone 781–238–7148; 

fax 781–238–7199.

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments 

regarding this proposal. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘AD Docket No. 

2000–NE–42–AD’’ in the subject line of 

your comments. If you want us to 

acknowledge receipt of your mailed 

comments, send us a self-addressed, 

stamped postcard with the docket 

number written on it; we will datestamp your postcard and mail it back to