Federal Register / Vol. 66, No. 248 / Thursday, December 27, 2001 / Rules and Regulations 66733

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–247–AD; Amendment

39–12572; AD 2001–26–08]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300 B2 Series Airplanes and Model

A300 B4–2C, B4–103, and B4–203

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all Airbus Model A300 B2

series airplanes and Model A300 B4–2C,

B4–103, and B4–203 series airplanes,

that requires identifying the types and

areas of repairs on the airplane between

frame 10 and frame 80, and performing

follow-on actions for certain repairs.

These actions are necessary to detect

and correct fatigue cracking of certain

repairs of the fuselage between frame 10

and frame 80, which could result in

reduced structural integrity of the

airplane. These actions are intended to

address the identified unsafe condition.

DATES: Effective January 31, 2002.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of January 31,

2002.

ADDRESSES: 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 Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

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: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to all Airbus Model

A300 B2 and B4 series airplanes was

published in the Federal Register on

August 28, 2001 (66 FR 45192). That

action proposed to require identifying

the types and areas of repairs on the

airplane between frame 10 and frame

80, and performing follow-on actions for

certain repairs.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Revise Applicability Statement of

Proposed AD

One commenter requests that the FAA

revise the applicability statement of the

proposed AD to exclude Model A300

B4–600 series airplanes. The commenter

states that this is an appropriate change

because French airworthiness directive

2000–261–312(B), dated June 28, 2000

(which is the French airworthiness

directive corresponding to the proposed

AD), and Airbus Service Bulletin A300–

53–0313, Revision 01, dated April 27,

1999 (which the proposed AD refers to

as the appropriate source of service

information for certain actions therein),

do not apply to Model A300 B4–600

series airplanes.

We concur with the commenter’s

request. We do not intend this AD to

apply to Model A300 B4–600 series

airplanes. However, based on the

commenter’s request, we recognize that

the identification of the affected

airplanes models in the proposed rule

could potentially confuse some owner/

operators. Therefore, we have revised

the applicability statement of this AD,

as well as the title and summary

sections in the preamble of this AD, to

clarify that this AD applies to all Airbus

Model A300 B2 series airplanes and

Model A300 B4–2C, B4–103, and B4–

203 series airplanes.

Request To Provide for Modified

Airplanes

One commenter, a supplemental type

certificate (STC) holder, requests that

we provide a different follow-on action

for airplanes that have been converted

from passenger airplanes to freighters

according to a specific STC. The

commenter explains that such

conversion results in increased loads on

certain fuselage skin panels on the

airplane. The commenter states that, if

an operator of a converted airplane

identifies an existing repair that is

subject to this AD on one of the fuselage

skin panels affected by the conversion,

the operator should contact the STC

holder for assistance in evaluating the

repair.

We do not concur that any change is

necessary in this regard, though we do

concur that the operator should contact

the STC holder for assistance in

evaluating the repair. Note 1 of this AD

specifies that, if an airplane has been

modified in such a way that the AD

requirements have been affected, the

owner/operator must request approval

of an alternative method of compliance

in accordance with paragraph (d) of this

AD. This provision would apply to

airplanes modified per the commenter’s

STC.

Conclusion

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the change

described previously. The FAA has

determined that this change will neither

increase the economic burden on any

operator nor increase the scope of the

AD.

Cost Impact

The FAA estimates that 13 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 2

work hours per airplane to accomplish

the required actions, and that the

average labor rate is $60 per work hour.

Based on these figures, the cost impact

of this AD on U.S. operators is estimated

to be $1,560, or $120 per airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted. The cost impact

figures discussed in AD rulemaking

actions represent only the time

necessary to perform the specific actions

actually required by the AD. These

figures typically do not include

incidental costs, such as the time

required to gain access and close up,

planning time, or time necessitated by

other administrative actions.

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)

66734 Federal Register / Vol. 66, No. 248 / Thursday, December 27, 2001 / Rules and Regulations

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:

2001–26–08 Airbus: Amendment 39–12572.

Docket 2000–NM–247–AD.

Applicability: All Model A300 B2 series

airplanes and Model A300 B4–2C, B4–103,

and B4–203 series airplanes, certificated in

any category.

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 (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 fatigue cracking of

certain repairs of the fuselage between frame

10 and frame 80, which could result in

reduced structural integrity of the airplane,

accomplish the following:

Identification of Repairs

(a) Before 10,000 total landings, or before

2,500 landings after the effective date of this

AD, whichever occurs later: Identify the

types and areas of repairs on the airplane

between frame 10 and frame 80, as specified

in Airbus Service Bulletin A300–53–0313,

Revision 01, dated April 27, 1999. Do the

actions per the Accomplishment Instructions

of the service bulletin. If none of the repairs

specified in the service bulletin are found, no

additional action is needed under this AD.

Follow-On Actions

(b) If, during the inspection, any repair is

found that meets the criteria specified in

Airbus Service Bulletin A300–53–0313,

Revision 01, dated April 27, 1999: Do either

an eddy current or ultrasonic inspection,

depending on the type of repair found, to

detect cracking of the applicable area

identified in Flow Chart 1, Figure 1, Sheet 1,

of the service bulletin. Do the inspection at

the time and in the manner specified in the

service bulletin. Based on the results of the

inspection, take the actions shown in the

following table:

TABLE 1.—FOLLOW-ON ACTIONS

If the following is found: Then— Per this schedule:

(1) No cracking ....................................... Repeat the inspection ............................................................ At least every 2,500 landings.

(2) Any cracking ...................................... Replace the repair per a method approved by either the

Manager, International Branch, ANM–116, FAA, Transport Airplane Directorate, or the Direction Ge ́ne ́rale de

l’Aviation Civile (DGAC) (or its delegated agent).

Before further flight.

Terminating Action

(c) Replacement of a repair that is specified

in Airbus Service Bulletin A300–53–0313,

Revision 01, dated April 27, 1999, per a

method approved by either the Manager,

International Branch, ANM–116, or the

DGAC (or its delegated agent), terminates the

requirements of this AD.

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 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

(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 provided in Table 1 and

paragraph (c) of this AD, the actions shall be

done in accordance with Airbus Service

Bulletin A300–53–0313, Revision 01, dated

April 27, 1999. 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 3: The subject of this AD is addressed

in French airworthiness directive 2000–261–

312(B), dated June 28, 2000.

Effective Date

(g) This amendment becomes effective on

January 31, 2002.

Issued in Renton, Washington, on

December 14, 2001.

Kalene C. Yanamura,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–31428 Filed 12–26–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–351–AD; Amendment

39–12573; AD 2001–26–09]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 767–200 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Boeing Model 767–