40874 Federal Register / Vol. 66, No. 151 / Monday, August 6, 2001 / Rules and Regulations

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To prevent chafing of the electrical wire

bundles, which could result in loss of flightcritical displays or system functions, and

potential fire, accomplish the following:

Inspection

(a) Within 25 flight hours after the effective

date of this AD, inspect the clearance

between the electrical bundles and air data

reference and reversionary switching panels,

in accordance with Astra (Israel Aircraft

Industries, Ltd.) Alert Service Bulletin 1125–

31A–236, dated April 16, 2001. If any

clearance is less than 0.25 inch (6.35 mm):

Prior to further flight, install additional

clamping to the electrical wire bundles in

accordance with the alert service bulletin.

Alternative Methods of Compliance

(b) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager,

International Branch, ANM–116, Transport

Airplane Directorate, FAA. Operators shall

submit their requests through an appropriate

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, International Branch, ANM–116.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

Special Flight Permits

(c) Special flight permits may be issued in

accordance with §§ 21.197 and 21.199 of the

Federal Aviation Regulations (14 CFR 21.197

and 21.199) to operate the airplane to a

location where the requirements of this AD

can be accomplished.

Incorporation by Reference

(d) The actions shall be done in accordance

with Astra (Israel Aircraft Industries, Ltd.)

Alert Service Bulletin 1125–31A–236, dated

April 16, 2001. This incorporation by

reference was approved by the Director of the

Federal Register in accordance with 5 U.S.C.

552(a) and 1 CFR part 51. Copies may be

obtained from Galaxy Aerospace Corporation,

One Galaxy Way, Fort Worth Alliance

Airport, Fort Worth, Texas 76177. Copies

may be inspected at the FAA, Transport

Airplane Directorate, 1601 Lind Avenue,

SW., Renton, Washington; or at the Office of

the Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

Note 3: The subject of this AD is addressed

in Israeli airworthiness directive 31–01–04–

10, dated May 8, 2001.

Effective Date

(e) This amendment becomes effective on

August 21, 2001.

Issued in Renton, Washington, on July 26,

2001.

Vi L. Lipski,

Manager, Transport Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 01–19255 Filed 8–3–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–NM–136–AD; Amendment

39–12369; AD 2001–16–01]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A330–301, –321, –322, –341, and –342

Series Airplanes, and Model A340

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain Airbus Model

A330–301, –321, –322, –341, and –342

series airplanes, and certain Model

A340 series airplanes. This action

requires repetitive inspections to detect

cracking of the aft cargo compartment

door, and corrective action if necessary.

This action also provides for optional

terminating action for the repetitive

inspections. This action is necessary to

detect and correct cracking of the aft

cargo compartment door, which could

result in reduced structural integrity of

the airplane. This action is intended to

address the identified unsafe condition.

DATES: Effective August 21, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of August 21,

2001.

Comments for inclusion in the Rules

Docket must be received on or before

September 5, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket 2001–NM–136–

AD, 1601 Lind Avenue, SW., Renton,

Washington 98055–4056. Comments

may be inspected at this location

between 9:00 a.m. and 3:00 p.m.,

Monday through Friday, except Federal

holidays. Comments may be submitted

via fax to (425) 227–1232. Comments

may also be sent via the Internet using

the following address: 9-anmiarcomment@faa.gov. Comments sent

via fax or the Internet must contain

‘‘Docket No. 2001–NM–136–AD’’ in the

subject line and need not be submitted

in triplicate. Comments sent via the

Internet as attached electronic files must

be formatted in Microsoft Word 97 for

Windows or ASCII text.

The service information referenced in

this AD may be obtained from Airbus

Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

This information may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW.,

Renton, Washington; or at the Office of

the Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

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: 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 A330–301, –321,

–322, –341, and –342 series airplanes,

and certain Model A340 series

airplanes. The DGAC advises that,

during fatigue tests, cracking was found

in several structural parts of the aft

cargo compartment door. The cracking

was detected between 42,944 and

67,605 simulated flights. This condition,

if not corrected, could result in reduced

structural integrity of the airplane.

Explanation of Relevant Service

Information

Airbus has issued Service Bulletins

A330–52–3043 (for Model A330 series

airplanes) and A340–52–4053 (for

Model A340 series airplanes), both

dated March 2, 2001. The service

bulletins describe procedures for

repetitive detailed visual inspections to

detect cracking of the aft cargo

compartment door, and corrective

action, if necessary. The DGAC

classified this service bulletin as

mandatory and issued French

airworthiness directives 2001–126(B)

and 2001–124(B), both dated April 4,

2001, to ensure the continued

airworthiness of these airplanes in

France.

Airbus has also issued Service

Bulletins A330–52–3044 (for Model

A330 series airplanes) and A340–52–

4054 (for Model A340 series airplanes),

both dated March 2, 2001. These service

bulletins describe procedures to modify

the aft cargo compartment door. The

Federal Register / Vol. 66, No. 151 / Monday, August 6, 2001 / Rules and Regulations 40875

modification involves either cold

expanding the fastener holes and

installing interference fit fasteners, or

reinforcing the affected area.

Accomplishment of the modification

eliminates the need to continue the

repetitive inspections.

FAA’s Conclusions

These airplane models are

manufactured in France and are type

certificated for operation in the United

States under the provisions of § 21.29 of

the Federal Aviation Regulations (14

CFR 21.19) and the applicable bilateral

airworthiness agreement. Pursuant to

this bilateral airworthiness agreement,

the DGAC has kept the FAA informed

of the situation described above. The

FAA has examined the findings of the

DGAC, reviewed all available

information, and determined that AD

action is necessary for products of this

type design that are certificated for

operation in the United States.

Explanation of Requirements of the

Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design that may be registered in the

United States at some time in the future,

this AD is being issued to detect and

correct cracking of the aft cargo

compartment door, which could result

in reduced structural integrity of the

airplane. This AD requires

accomplishment of the actions specified

in Service Bulletins A330–52–3043 and

A340–52–4053, except as discussed

below in ‘‘Differences Between the AD

and the Service Bulletins.’’ This AD also

provides for optional terminating action

for the repetitive inspections.

Operators should note that, to be

consistent with the findings of the

DGAC, the FAA has determined that the

repetitive inspections required by this

AD can be allowed to continue in lieu

of accomplishment of a terminating

action. Additionally, the FAA has

determined that, for certain instances

where cracking is detected, the repair

may be deferred for a specified period

of time. In making these determinations,

the FAA considers that, in the case of

this AD, long-term continued

operational safety will be adequately

assured by accomplishing the repetitive

inspections to detect cracking before it

represents a hazard to the airplane, and

by accomplishing repairs within the

specified time limits.

Interim Action

This is considered to be interim

action until final action is identified, at

which time the FAA may consider

further rulemaking.

Differences Between the AD and the

Service Bulletins

Although Service Bulletins A330–52–

3043 and A340–52–4053 specify that

the manufacturer may be contacted for

disposition of certain repair conditions,

this AD requires the repair of those

conditions to be accomplished in

accordance with a method approved by

either the FAA or the DGAC (or its

delegated agent). In light of the type of

repair that would be required to address

the identified unsafe condition, and in

consonance with existing bilateral

airworthiness agreements, the FAA has

determined that, for this AD, a repair

approved by either the FAA or the

DGAC would be acceptable for

compliance with the requirements of

this AD.

Cost Impact

None of the airplanes affected by this

action are on the U.S. Register. All

airplanes included in the applicability

of this rule currently are operated by

non-U.S. operators under foreign

registry; therefore, they are not directly

affected by this AD action. However, the

FAA considers that this rule is

necessary to ensure that the unsafe

condition is addressed in the event that

any of these subject airplanes are

imported and placed on the U.S.

Register in the future.

Should an affected airplane be

imported and placed on the U.S.

Register in the future, it would take

approximately 8 work hours to

accomplish the required inspection, at

an average labor rate of $60 per work

hour. Based on these figures, the cost

impact of this AD would be $480 per

airplane, per inspection cycle.

Should an operator elect to

accomplish the optional terminating

action, the cost would vary depending

on the kit installed. It would take

approximately 2 to 45 work hours to

accomplish the modification, at an

average labor rate of $60 per work hour.

Required parts would cost

approximately $60 to $5,010 per

airplane. Based on these figures, the cost

impact of this AD would be as little as

$180, and as much as $7,710, per

airplane.

Determination of Rule’s Effective Date

Since this AD action does not affect

any airplane that is currently on the

U.S. register, it has no adverse economic

impact and imposes no additional

burden on any person. Therefore, prior

notice and public procedures hereon are

unnecessary and the amendment may be

made effective in less than 30 days after

publication in the Federal Register.

Comments Invited

Although this action is in the form of

a final rule and was not preceded by

notice and opportunity for public

comment, comments are invited on this

rule. Interested persons are invited to

comment on this rule by submitting

such written data, views, or arguments

as they may desire. Communications

shall identify the Rules Docket number

and be submitted in triplicate to the

address specified under the caption

ADDRESSES. All communications

received on or before the closing date

for comments will be considered, and

this rule may be amended in light of the

comments received. Factual information

that supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Submit comments using the following

format:

• Organize comments issue-by-issue.

For example, discuss a request to

change the compliance time and a

request to change the service bulletin

reference as two separate issues.

• For each issue, state what specific

change to the proposed AD is being

requested.

• Include justification (e.g., reasons or

data) for each request.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report that

summarizes each FAA-public contact

concerned with the substance of this AD

will be filed in the Rules Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this rule must

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket 2001–NM–136–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Regulatory Impact

The regulations adopted herein 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. Therefore, it is

determined that this final rule does not

40876 Federal Register / Vol. 66, No. 151 / Monday, August 6, 2001 / Rules and Regulations

have federalism implications under

Executive Order 13132.

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under 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. A final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends part 39 of the

Federal Aviation Regulations (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. Section 39.13 is amended by

adding the following new airworthiness

directive:

2001–16–01 Airbus Industrie: Amendment

39–12369. Docket 2001–NM–136–AD.

Applicability: The following airplanes,

certificated in any category:

—Model A330–301, –321, –322, –341, and

–342 series airplanes; excluding those that

have received Airbus Modification 44852

(reference Airbus Service Bulletin A330–52–

3044, dated March 2, 2001) or Airbus

Modification 44854.

—Model A340 series airplanes, excluding

those that have received Airbus Modification

44852 (reference Airbus Service Bulletin

A340–52–4054, dated March 2, 2001) or

Airbus Modification 44854.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise modified, altered, or repaired in

the area subject to the requirements of this

AD. For airplanes that have been modified,

altered, or repaired so that the performance

of the requirements of this AD is affected, the

owner/operator must request approval for an

alternative method of compliance in

accordance with paragraph (d) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and, if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To detect and correct cracking of the aft

cargo compartment door, which could result

in reduced structural integrity of the

airplane, accomplish the following:

Inspection

(a) Before the accumulation of 12,000 total

flight cycles, perform a detailed visual

inspection to detect cracking of the aft cargo

compartment door, in accordance with

Airbus Service Bulletin A330–52–3043 (for

Model A330 series airplanes) or A340–52–

4053 (for Model A340 series airplanes), both

dated March 2, 2001; as applicable. Perform

applicable follow-on and corrective actions at

the applicable threshold in accordance with

the applicable service bulletin, except as

required by paragraph (b) of this AD. Repeat

the inspection thereafter at least every 4,000

flight cycles.

Note 2: For the purposes of this AD, a

detailed visual inspection is defined as: ‘‘An

intensive visual examination of a specific

structural area, system, installation, or

assembly to detect damage, failure, or

irregularity. Available lighting is normally

supplemented with a direct source of good

lighting at intensity deemed appropriate by

the inspector. Inspection aids such as mirror,

magnifying lenses, etc., may be used. Surface

cleaning and elaborate access procedures

may be required.’’

(b) If any crack is found during any

inspection required by paragraph (a) of this

AD, and the applicable service bulletin

specifies to contact Airbus for appropriate

action: Prior to further flight, repair per a

method approved by either the Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate; or the

Direction Generale de l’Aviation Civile

(DGAC) (or its delegated agent).

Optional Terminating Action

(c) Modification of the aft cargo

compartment door terminates the repetitive

inspections required by this AD, if the

modification is accomplished in accordance

with Airbus Service Bulletin A330–52–3044

(for Model A330 series airplanes) or A340–

52–4054 (for Model A340 series airplanes),

both dated March 2, 2001; as applicable.

Alternative Methods of Compliance

(d) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager,

International Branch, ANM–116. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, International Branch,

ANM–116.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

Special Flight Permits

(e) Special flight permits may be issued in

accordance with §§ sections 21.197 and

21.199 of the Federal Aviation Regulations

(14 CFR 21.197 and 21.199) to operate the

airplane to a location where the requirements

of this AD can be accomplished.

Incorporation by Reference

(f) Except as required by paragraph (b) of

this AD: The inspection must be done in

accordance with Airbus Service Bulletin

A330–52–3043, dated March 2, 2001; or

Airbus Service Bulletin A340–52–4053,

dated March 2, 2001; as applicable. The

modification, if accomplished, must be done

in accordance with Airbus Service Bulletin

A330–52–3044, dated March 2, 2001; or

Airbus Service Bulletin A340–52–4054,

dated March 2, 2001; as applicable. This

incorporation by reference was approved by

the Director of the Federal Register in

accordance with 5 U.S.C. 552(a) and 1 CFR

part 51. Copies may be obtained from Airbus

Industrie, 1 Rond Point Maurice Bellonte,

31707 Blagnac Cedex, France. Copies may be

inspected at the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

Note 4: The subject of this AD is addressed

in French airworthiness directives 2001–

126(B) and 2001–124(B), both dated April 4,

2001.

Effective Date

(g) This amendment becomes effective on

August 21, 2001.

Issued in Renton, Washington, on July 26,

2001.

Vi L. Lipski,

Manager, Transport Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 01–19257 Filed 8–3–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–340–AD; Amendment

39–12366; AD 2001–15–31]

RIN 2120–AA64

Airworthiness Directives; Bombardier

Model DHC–8–311 and –315 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Bombardier Model

DHC–8–311 and –315 series airplanes.

This action requires replacement of the

door stops on the baggage bulkhead