23838 Federal Register / Vol. 66, No. 91 / Thursday, May 10, 2001 / Rules and Regulations

Inspector, who may add comments and then

send it to the Manager, Atlanta ACO.

(2) Alternative methods of compliance,

approved previously in accordance with AD

95–01–06 R1, amendment 39–9449, are

approved as alternative methods of

compliance with paragraphs (a) and (b) of

this AD.

Note 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Atlanta ACO.

Special Flight Permits

(d) 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

(e) The actions shall be done in accordance

with Pemco Alert Service Letter 737–53–

0003, Revision 3, dated December 22, 1994;

Pemco Service Bulletin 737–53–0003,

Revision 4, dated February 22, 1995, or

Pemco Service Bulletin 737–53–0003,

Revision 5, dated March 25, 1999; as

applicable.

(1) The incorporation by reference of

Pemco Service Bulletin 737–53–0003,

Revision 4, dated February 22, 1995; and

Pemco Service Bulletin 737–53–0003,

Revision 5, dated March 25, 1999; is

approved by the Director of the Federal

Register in accordance with 5 U.S.C. 552(a)

and 1 CFR part 51.

(2) The incorporation by reference of

Pemco Alert Service Letter 737–53–0003,

Revision 3, dated December 22, 1994, was

approved previously by the Director of the

Federal Register as of January 24, 1995 (60 FR

2323, January 9, 1995).

(3) Copies may be obtained from Pemco

Aeroplex, Inc., P.O. Box 2287, Birmingham,

Alabama 35201–2287. Copies may be

inspected at the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Atlanta ACO,

One Crown Center, 1895 Phoenix Boulevard,

suite 450, Atlanta, Georgia; or at the Office

of the Federal Register, 800 North Capitol

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

Effective Date

(f) This amendment becomes effective on

June 14, 2001.

Issued in Renton, Washington, on May 1,

2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–11455 Filed 5–9–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–389–AD; Amendment

39–12221; AD 2001–09–14]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A330–243, –341, –342, and –343 Series

Airplanes Equipped With Rolls Royce

Trent 700 Series Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to Airbus Model A330–243,

–341, –342, and –343 series airplanes

equipped with Rolls Royce Trent 700

series engines. This action requires

repetitive inspections of certain

components, and corrective action, if

necessary. This action is necessary to

detect and correct fatigue cracking of the

hinge assemblies and the 12 o’clock

beam structure of the thrust reverser Cduct, which could cause failure of the

thrust reverser hinge, resulting in

separation of the thrust reverser from

the airplane. This action is intended to

address the identified unsafe condition.

DATES: Effective May 25, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 25,

2001.

Comments for inclusion in the Rules

Docket must be received on or before

June 11, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

389–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9 a.m. and 3 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. 2000–NM–389–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: Tim

Backman, Aerospace Engineer,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2797;

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

Airbus Model A330–243, –341, –342,

and –343 series airplanes equipped with

Rolls Royce Trent 700 series engines.

The DGAC advises that, during flight

tests, unexpectedly high fatigue loads

were measured on the hinges integrated

on the 12 o’clock beam which forms the

upper edge of the thrust reverser C-duct.

The hinges are unable to withstand

these high fatigue loads for the design

life of the airplane. Resulting fatigue

cracks, if not detected and corrected,

could cause failure of the thrust reverser

hinge, which could result in separation

of the thrust reverser from the airplane.

Explanation of Relevant Service

Information

Airbus has issued Service Bulletin

A330–78–3006, Revision 05, dated

March 6, 2001, which describes

procedures for a general visual

inspection of the hinge assemblies and

the beam structure of the upper extreme

edge of the thrust reverser unit C-duct

for cracks, and corrective action, if

necessary; a detailed visual inspection,

if applicable, of hinges 2, 3, 4, and 5 in

the same area for cracks, and corrective

action, if necessary; and repetitions of

these inspections, as applicable, at

applicable intervals. Accomplishment of

the actions specified in the service

bulletin is intended to adequately

address the identified unsafe condition.

The DGAC classified this service

bulletin as mandatory and issued

French airworthiness directive 1997–

118–047(B) R2, dated September 20,

2000, in order to assure the continued

airworthiness of these airplanes in

France.

Airbus Service Bulletin A330–78–

3006, Revision 05, dated March 6, 2001,

references Rolls Royce Service Bulletin

RB.211–78–B115, Revision 2, dated

October 29, 1999, as an additional

source of service information for

Federal Register / Vol. 66, No. 91 / Thursday, May 10, 2001 / Rules and Regulations 23839

accomplishment of the inspections and

corrective actions.

FAA’s Conclusions

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 21.19) 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 fatigue cracking of the hinge

assemblies and the 12 o’clock beam

structure of the thrust reverser C-duct,

which could cause failure of the thrust

reverser hinge, resulting in separation of

the thrust reverser from the airplane.

This AD requires accomplishment of the

actions specified in the Airbus service

bulletin described previously.

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 require

approximately 5 work hours to

accomplish the required inspections, at

an average labor rate of $60 per work

hour. Based on these figures, the cost

impact of this AD would be $300 per

airplane, per inspection cycle.

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 Number 2000–NM–389–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

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:

2001–09–14 Airbus Industrie: Amendment

39–12221. Docket 2000–NM–389–AD.

Applicability: Model A330–243, –341,

–342 and –343 series airplanes; certificated

in any category; that are equipped with Rolls

Royce Trent 700 series engines.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

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 (b) 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.

23840 Federal Register / Vol. 66, No. 91 / Thursday, May 10, 2001 / Rules and Regulations

Compliance: Required as indicated, unless

accomplished previously.

To detect and correct fatigue cracking of

the hinge assemblies and the 12 o’clock beam

structure of the thrust reverser C-duct, which

could cause failure of the thrust reverser

hinge, resulting in separation of the thrust

reverser from the airplane, accomplish the

following:

Initial and Repetitive Inspections

(a) Perform a general visual inspection of

the hinge assemblies and the 12 o’clock beam

structure of the right and left thrust reversers

for cracks, in accordance with Airbus Service

Bulletin A330–78–3006, Revision 05, dated

March 6, 2001, according to the criteria in

Table 1 of this AD, below:

TABLE 1—INITIAL INSPECTION

If— Then inspect—

Neither Airbus Modification 46879 nor

47358 has been

embodied on the

airplane.

Before the accumulation of 1,200 total

flight cycles, or

within 6 months

after the effective

date of this AD,

whichever occurs

first.

Either Airbus Modification 46879 or

47358 have been

embodied on the

airplane.

Before the accumulation of 2,000 total

flight cycles, or 6

months after the effective date of this

AD, whichever occurs first.

(1) If no crack is found during the general

visual inspection required by paragraph (a) of

this AD, before further flight, perform a

detailed visual inspection of the lugs of

hinges 2, 3, 4, and 5 of the right and left

thrust reversers for cracks in accordance with

Airbus Service Bulletin A330–78–3006,

Revision 05, dated March 6, 2001.

(i) If no crack is found as a result of the

detailed visual inspection mandated by

paragraph (a)(1) of this AD, repeat the general

visual inspection mandated by paragraph (a)

of this AD according to the schedule in Table

2 of this AD.

(ii) If a crack is found as a result of the

detailed visual inspection mandated by

paragraph (a)(1) of this AD:

(A) Before further flight, replace the

affected thrust reverser with a new or

serviceable thrust reverser in accordance

with Airbus Service Bulletin A330–78–3006,

Revision 05, dated March 6, 2001.

(B) Repeat the general visual inspection

mandated in paragraph (a) of this AD

according to the schedule in Table 2 of this

AD.

(2) If a crack is found during the general

visual inspection required by paragraph (a) of

this AD, accomplish the actions required by

paragraphs (a)(2)(i) and (a)(2)(ii) of this AD.

(i) Before further flight, replace the affected

thrust reverser with a new or serviceable

thrust reverser in accordance with Airbus

Service Bulletin A330–78–3006, Revision 05,

dated March 6, 2001.

(ii) Repeat the general visual inspection

mandated in paragraph (a) of this AD

according to the schedule in Table 2 of this

AD, below:

TABLE 2.—REPETITIVE INSPECTIONS

If—

Then repeat the inspection at intervals

not to exceed—

Neither Airbus Modification 46879 nor

47358 has been

embodied on the

airplane.

1,200 flight cycles.

Either Airbus Modification 46879 or

47358 has been

embodied on the

airplane.

2,000 flight cycles.

Note 2: For the purposes of this AD, a

general visual inspection is defined as: ‘‘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 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.’’

Note 3: 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 a

mirror, magnifying lenses, etc., may be used.

Surface cleaning and elaborate access

procedures may be required.’’

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 4: 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 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

(d) The actions shall be done in accordance

with Airbus Service Bulletin A330–78–3006,

Revision 05, dated March 6, 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 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 5: The subject of this AD is addressed

in French airworthiness directive 1997–118–

047(B) R2, dated September 20, 2000.

Effective Date

(e) This amendment becomes effective on

May 25, 2001.

Issued in Renton, Washington, on April 30,

2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–11223 Filed 5–9–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–164–AD; Amendment

39–12225; AD 2001–09–18]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model DC–9–80 Series

Airplanes and Model MD–88 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain McDonnell

Douglas Model DC–9–80 series

airplanes and Model MD–88 airplanes,

that currently requires a one-time

inspection to detect cracking of the

main landing gear (MLG) pistons, and

repair or replacement of the pistons

with new or serviceable parts, if

necessary. This amendment requires,

among other actions, repetitive dye

penetrant and magnetic particle

inspections to detect cracks of the MLG

pistons; repair and replacement of

discrepant parts; and installation of a

preventative modification; as

applicable. This amendment also

provides for an optional terminating

action for certain MLG pistons. This

amendment is prompted by additional

reports of failure of the MLG pistons

during towing of the airplanes. The

actions specified by this AD are

intended to prevent fatigue cracking of

the MLG pistons, which could result in