Federal Register / Vol. 65, No. 197 / Wednesday, October 11, 2000 / Rules and Regulations 60349

fuselage frame(s) is greater than the limits

shown in the 757 Structural Repair Manual,

accomplish the repair in accordance with a

method approved by the Manager, Seattle

Aircraft Certification Office (ACO), FAA.

Reactivate the cargo loader system only in

accordance with a method approved by the

Manager, Seattle ACO. Operators shall

submit their requests through an appropriate

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, Seattle ACO.

Alternative Methods of Compliance

(c) 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, Seattle

ACO. Operators shall submit their requests

through an appropriate FAA Principal

Maintenance Inspector, who may add

comments and then send it to the Manager,

Seattle ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle 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) Except as provided by paragraph (b) of

this AD, the actions shall be done in

accordance with Boeing Alert Service

Bulletin 757–25A0233, dated August 10,

2000. 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 Boeing Commercial Airplane Group,

P.O. Box 3707, Seattle, Washington 98124–

2207. 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.

Effective Date

(f) This amendment becomes effective on

October 26, 2000.

Issued in Renton, Washington, on

September 29, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–25532 Filed 10–10–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–207–AD; Amendment

39–11926; AD 2000–20–15]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300 and A300–600 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A300 and A300–600 series airplanes,

that requires a high frequency eddy

current (HFEC) inspection to detect

cracking of the rear fittings of fuselage

frame FR40 at stringer 27, and repetitive

inspections or repair, as applicable. In

lieu of accomplishing the repetitive

inspections, this amendment requires a

modification that would allow the

inspection to be deferred for a certain

period of time. This amendment is

prompted by issuance of mandatory

continuing airworthiness information by

a foreign civil airworthiness authority.

The actions specified by this AD are

intended to detect and correct fatigue

cracking of the rear fittings of fuselage

frame FR40 at stringer 27, which could

result in reduced structural integrity of

the airplane.

DATES: Effective November 15, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of November

15, 2000.

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:

Norman B. Martenson, Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

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 certain Airbus

Model A300 and A300–600 series

airplanes was published in the Federal

Register on May 10, 2000 (65 FR 30033).

That action proposed to require a high

frequency eddy current (HFEC)

inspection to detect cracking of the rear

fittings of fuselage frame FR40 at

stringer 27, and repetitive inspections or

repair, as applicable. In lieu of

accomplishing the repetitive

inspections, that action proposed to

require a modification that would allow

the inspection to be deferred for a

certain period of time.

Comment Received

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

single comment received.

Request To Revise Compliance Times

The commenter questions the

compliance times specified in the

proposed AD. The commenter notes that

there are small discrepancies between

the compliance thresholds

recommended in the referenced service

bulletins for Airbus Model A300 B2,

B4–100, and B4–600 series airplanes,

and the thresholds specified by the

proposed AD. The commenter suggests

that it would be preferable for the

compliance times in the AD to be in line

with those in the service bulletins, since

this would avoid confusion by operators

and reduce the number of questions that

may be raised.

The FAA concurs. For the reasons

stated in the proposed AD, the FAA

specified fixed compliance times for

accomplishment of the required actions,

rather than permitting use of the

‘‘adjustment-for-range’’ formula for

calculating compliance times. During

discussions with the manufacturer to

determine an interim method of

calculating the fixed compliance times,

flight cycle thresholds and intervals for

certain models were recommended for

reduction from those in the service

bulletins, based on the average flight

times of those models. Subsequently, a

revised method for calculation of such

fixed compliance times was defined by

the manufacturer. This method allows

use of the flight cycle thresholds and

intervals specified in the referenced

service bulletins.

The FAA has determined that,

consistent with the manufacturer’s

revised method for calculation of fixed

compliance times, the flight cycle

thresholds and intervals recommended

in the referenced service bulletins

constitute acceptable compliance times

for this AD. The final rule has been

60350 Federal Register / Vol. 65, No. 197 / Wednesday, October 11, 2000 / Rules and Regulations

revised accordingly. Because the flight

cycle compliance times for certain

airplane models have been increased

rather than reduced, and the flight hour

compliance times are unchanged, such

revision imposes no additional

restrictions on operators.

Conclusion

After careful review of the available

data, including the comment 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 85 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 1

work hour per airplane to accomplish

the required HFEC inspection, and that

the average labor rate is $60 per work

hour. Based on these figures, the cost

impact of the inspection on U.S.

operators is estimated to be $5,100, or

$60 per airplane, per inspection cycle.

Should an operator be required to

accomplish the modification rather than

the repetitive inspections, it will take

approximately 3 work hours per

airplane to accomplish. Based on these

figures, the cost impact of the

modification required by this AD on

U.S. operators is estimated to be

$15,300, or $180 per airplane.

The cost impact figures discussed

above are 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)

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:

2000–20–15 Airbus Industrie: Amendment

39–11926. Docket 98–NM–207–AD.

Applicability: Model A300 and A300–600

series airplanes, on which Airbus

Modification 11525 has not been

accomplished; certificated in any category.

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 (h) 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

the rear fittings of fuselage frame FR40 at

stringer 27, which could result in reduced

structural integrity of the airplane,

accomplish the following:

Inspection

(a) Perform a high frequency eddy current

(HFEC) inspection to detect cracks in the

stiffeners at stringer 27 of the rear fitting of

fuselage frame FR40, left and right, in

accordance with Airbus Service Bulletin

A300–53–0332, dated November 24, 1997

(for Model A300 B2 and B4 series airplanes),

or Airbus Service Bulletin A300–57–6075,

dated November 24, 1997 (for Model A300–

600 series airplanes); as applicable; at the

applicable time specified in paragraph (a)(1),

(a)(2), (a)(3), (a)(4), (a)(5), (a)(6), (a)(7), or

(a)(8) of this AD.

(1) For Model A300 B2 series airplanes that

have accumulated less than 26,000 total

flight cycles as of the effective date of this

AD: Inspect at the earlier of the times

specified in paragraphs (a)(1)(i) and (a)(1)(ii)

of this AD.

(i) Prior to the accumulation of 11,600 total

flight cycles, or within 3,000 flight cycles

after the effective date of this AD, whichever

occurs later.

(ii) Prior to the accumulation of 14,300

total flight hours, or within 3,800 flight hours

after the effective date of this AD, whichever

occurs later.

(2) For Model A300 B2 series airplanes that

have accumulated 26,000 or more total flight

cycles as of the effective date of this AD:

Inspect within 2,200 flight cycles or 2,800

flight hours after the effective date of this AD,

whichever occurs first.

(3) For Model A300 B4–100 series

airplanes that have accumulated less than

20,000 total flight cycles as of the effective

date of this AD: Inspect at the earlier of the

times specified in paragraphs (a)(3)(i) and

(a)(3)(ii) of this AD.

(i) Prior to the accumulation of 9,200 total

flight cycles, or within 3,000 flight cycles

after the effective date of this AD, whichever

occurs later.

(ii) Prior to the accumulation of 15,700

total flight hours, or within 5,800 flight hours

after the effective date of this AD, whichever

occurs later.

(4) For Model A300 B4–100 series

airplanes that have accumulated 20,000 or

more total flight cycles as of the effective date

of this AD: Inspect within 1,800 flight cycles

or 3,400 flight hours after the effective date

of this AD, whichever occurs first.

(5) For Model A300 B4–200 series

airplanes that have accumulated less than

14,000 total flight cycles as of the effective

date of this AD: Inspect at the earlier of the

times specified in paragraphs (a)(5)(i) and

(a)(5)(ii) of this AD.

(i) Prior to the accumulation of 8,300 total

flight cycles, or within 3,000 flight cycles

after the effective date of this AD, whichever

occurs later.

(ii) Prior to the accumulation of 17,200

total flight hours, or within 6,200 flight hours

after the effective date of this AD, whichever

occurs later.

(6) For Model A300 B4–200 series

airplanes that have accumulated 14,000 or

more total flight cycles as of the effective date

of this AD: Inspect within 1,700 flight cycles

or 3,500 flight hours after the effective date

of this AD, whichever occurs first.

Federal Register / Vol. 65, No. 197 / Wednesday, October 11, 2000 / Rules and Regulations 60351

(7) For Model A300–600 series airplanes

that have accumulated less than 18,000 total

flight cycles as of the effective date of this

AD: Inspect at the earlier of the times

specified in paragraphs (a)(7)(i) and (a)(7)(ii)

of this AD.

(i) Prior to the accumulation of 6,200 total

flight cycles, or within 2,700 flight cycles

after the effective date of this AD, whichever

occurs later.

(ii) Prior to the accumulation of 15,100

total flight hours, or within 7,000 flight hours

after the effective date of this AD, whichever

occurs later.

(8) For Model A300–600 series airplanes

that have accumulated 18,000 or more total

flight cycles as of the effective date of this

AD: Inspect within 1,400 flight cycles or

3,600 flight hours after the effective date of

this AD, whichever occurs first.

Repetitive Inspections

(b) If no crack is detected during the initial

inspection required by paragraph (a) of this

AD, except as provided by paragraph (e) of

this AD, repeat the inspection required by

paragraph (a) of this AD at the time specified

in paragraph (b)(1), (b)(2), (b)(3), or (b)(4) of

this AD, as applicable.

(1) For Model A300 B2 series airplanes:

Repeat at intervals not to exceed 2,200 flight

cycles or 2,700 flight hours, whichever

occurs first.

(2) For Model A300 B4–100 series

airplanes: Repeat at intervals not to exceed

1,800 flight cycles or 3,000 flight hours,

whichever occurs first.

(3) For Model A300 B4–200 series

airplanes: Repeat at intervals not to exceed

1,700 flight cycles or 3,500 flight hours,

whichever occurs first.

(4) For Model A300–600 series airplanes:

Repeat at intervals not to exceed 1,400 flight

cycles or 3,400 flight hours, whichever

occurs first.

Repair Cracking Found During Inspections

(c) If any crack is found during any

inspection required by paragraph (a) or (b) of

this AD and the crack is less than 0.787

inches long, prior to further flight, repair in

accordance with Airbus Service Bulletin

A300–53–0332, dated November 24, 1997

(for Model A300 B2 and B4 series airplanes),

or Airbus Service Bulletin A300–57–6075,

dated November 24, 1997 (for Model A300–

600 series airplanes); as applicable. Perform

the inspection required by paragraph (a) of

this AD one more time at the time specified

in paragraph (c)(1), (c)(2), (c)(3), or (c)(4) of

this AD, as applicable, and accomplish the

actions specified in paragraph (f) or (g) of this

AD, as applicable.

(1) For Model A300 B2 series airplanes:

Within 44,500 flight cycles or 54,600 flight

hours after accomplishment of the repair,

whichever occurs first.

(2) For Model A300 B4–100 series

airplanes: Within 35,200 flight cycles or

56,700 flight hours after accomplishment of

the repair, whichever occurs first.

(3) For Model A300 B4–200 series

airplanes: Within 31,900 flight cycles or

66,100 flight hours after accomplishment of

the repair, whichever occurs first.

(4) For Model A300–600 series airplanes:

Within 23,700 flight cycles or 57,500 flight

hours after accomplishment of the repair,

whichever occurs first.

(d) If any crack is found during any

inspection required by paragraph (a) or (b) of

this AD and the crack is 0.787 inches long

or more, prior to further flight, repair it in

accordance with a method approved by 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). For a repair

method to be approved by the Manager,

International Branch, ANM–116, as required

by this paragraph, the Manager’s approval

letter must specifically reference this AD.

Deferral of Repetitive Inspections by

Modification

(e) In lieu of accomplishing the

requirements of paragraph (b) of this AD,

prior to further flight after accomplishing the

inspection required by paragraph (a) of this

AD, modify the rear fitting at stringer 27 at

FR40 of the center fuselage in accordance

with Airbus Service Bulletin A300–53–0333,

dated November 24, 1997 (Model A300 B2

and B4 series airplanes), or Airbus Service

Bulletin A300–57–6076, dated November 24,

1997 (for Model A300–600 series airplanes);

as applicable. Following accomplishment of

the modification, perform the inspection

required by paragraph (a) of this AD one

more time at the time specified in paragraph

(e)(1), (e)(2), (e)(3), or (e)(4) of this AD, as

applicable, and accomplish the actions

specified in paragraph (f) or (g) of this AD,

as applicable.

(1) For Model A300 B2 series airplanes:

Within 59,600 flight cycles or 73,100 flight

hours after accomplishment of the

modification, whichever occurs first.

(2) For Model A300 B4–100 series

airplanes: Within 47,100 flight cycles or

75,900 flight hours after accomplishment of

the modification, whichever occurs first.

(3) For Model A300 B4–200 series

airplanes: Within 42,700 flight cycles or

88,400 flight hours after accomplishment of

the modification, whichever occurs first.

(4) For Model A300–600 series airplanes:

Within 31,700 flight cycles or 76,800 flight

hours after accomplishment of the

modification, whichever occurs first.

Follow-on Action if No Cracking Is Found

During Certain Inspections

(f) If no crack is detected during the

inspection required by paragraph (c) or (e) of

this AD, prior to further flight, contact the

Manager, International Branch, ANM–116, or

the DGAC (or its delegated agent) for the next

inspection time(s), and repeat the

inspection(s) thereafter at those times.

Repair for Cracking Found During a Certain

Inspection

(g) If any crack is detected during the

inspection required by paragraph (c) or (e) of

this AD, prior to further flight, repair it in

accordance with a method approved by the

Manager, International Branch, ANM–116, or

the DGAC (or its delegated agent). For a

repair method to be approved by the

Manager, International Branch, ANM–116, as

required by this paragraph, the Manager’s

approval letter must specifically reference

this AD.

Alternative Methods of Compliance

(h) 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

(i) 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

(j) Except as required by paragraphs (d), (f),

and (g) of this AD, the actions shall be done

in accordance with Airbus Service Bulletin

A300–53–0332, dated November 24, 1997;

Airbus Service Bulletin A300–57–6075,

dated November 24, 1997; Airbus Service

Bulletin A300–53–0333, dated November 24,

1997; or Airbus Service Bulletin A300–57–

6076, dated November 24, 1997; 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 3: The subject of this AD is addressed

in French airworthiness directive 98–028–

242 (B), dated January 28, 1998.

(k) This amendment becomes effective on

November 15, 2000.

Issued in Renton, Washington, on

September 29, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–25533 Filed 10–10–00; 8:45 am]

BILLING CODE 4910–13–P