5756 Federal Register / Vol. 65, No. 25 / Monday, February 7, 2000 / Rules and Regulations

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:

2000–03–01 Boeing: Amendment 39–11558.

Docket 99–NM–88–AD.

Applicability: Model 747–100 and –200

series airplanes, listed in Boeing Service

Bulletin 747–57–2305, Revision 1, dated

January 21, 1999; 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

the upper and lower chords of the wing front

spar, which could result in reduced

structural capability and possible fuel

leakage onto an engine and a resultant fire,

accomplish the following:

Inspections and Corrective Action

(a) Prior to the accumulation of 12,000 total

flight cycles, or within 24 months after the

effective date of this AD, whichever occurs

later, accomplish an ultrasonic inspection for

cracking of the upper and lower chord of the

wing front spar, in accordance with Boeing

Service Bulletin 747–57–2305, Revision 1,

dated January 21, 1999.

Note 2: Accomplishment of an open hole

high frequency eddy current inspection in

accordance with Figure 6 of Boeing Service

Bulletin 747–57–2305, Revision 1, dated

January 21, 1999, is acceptable for

compliance with the inspection requirement

of paragraph (a) of this AD.

(1) If no cracking is found, repeat this

inspection thereafter at intervals not to

exceed 6,000 flight cycles, until the

requirements of paragraph (c) of this AD have

been accomplished.

(2) If any cracking is found, prior to further

flight, accomplish ‘‘Part 2—Terminating

Action’’ of the Accomplishment Instructions

of the service bulletin, except as provided by

paragraph (b) of this AD. Accomplishment of

this action constitutes terminating action for

the requirements of this AD.

(b) During accomplishment of the

terminating action required by paragraph

(a)(2) of this AD, if any crack is found in the

upper chord that is outside the limits

specified in Boeing Service Bulletin 747–57–

2305, Revision 1, dated January 21, 1999; or

if any crack is found in the lower chord; prior

to further flight, repair in accordance with a

method approved by the Manager, Seattle

Aircraft Certification Office (ACO), FAA,

Transport Airplane Directorate; or in

accordance with data meeting the type

certification basis of the airplane approved

by a Boeing Company Designated

Engineering Representative who has been

authorized by the FAA to make such

findings. For a repair method to be approved

by the Manager, Seattle ACO, as required by

this AD, the Manager’s approval letter must

specifically reference this AD.

Optional Terminating Action

(c) Accomplishment of ‘‘Part 2—

Terminating Action’’ of the Accomplishment

Instructions of Boeing Service Bulletin 747–

57–2305, Revision 1, dated January 21, 1999,

constitutes terminating action for the

requirements of this AD.

Note 3: Accomplishment of the wing and

strut modification specified in AD 95–10–16,

amendment 39–9233, or AD 95–13–07,

amendment 39–9287, or the optional

terminating action specified in AD 99–10–09,

amendment 39–11162, constitutes

terminating action for the repetitive

inspections required by paragraph (a) of this

AD, provided that an HFEC inspection of

subject fastener holes has been accomplished

in accordance with Boeing 747 NonDestructive Test Manual D6–7170, Part 6,

Subject 51–00–00, Figure 16, prior to

oversizing of the holes in accordance with

AD 95–10–16, AD 95–13–07, or AD 99–10–

09, and the holes were found to be free of

cracks, corrosion, or damage.

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, 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 4: 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

(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 by paragraph (c) of

this AD, the actions shall be done in

accordance with Boeing Service Bulletin

747–57–2305, Revision 1, dated January 21,

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 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.

(g) This amendment becomes effective on

March 13, 2000.

Issued in Renton, Washington, on January

31, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–2468 Filed 2–4–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–16–AD; Amendment

39–11557; AD 2000–02–39]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300 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

A300 series airplanes. This action

requires either a one-time ultrasonic

inspection, or repetitive visual

inspections and eventual ultrasonic

inspection, to detect cracking of the

longitudinal skin splice above the midpassenger door panels, and corrective

actions, if necessary. This amendment is

prompted by issuance of mandatory

continuing airworthiness information by

a foreign civil airworthiness authority.

The actions specified in this AD are

intended to detect and correct cracking

of the longitudinal skin splice above the

mid-passenger door panels, which could

result in reduced structural integrity of

the fuselage pressure vessel.

DATES: Effective February 22, 2000.

Federal Register / Vol. 65, No. 25 / Monday, February 7, 2000 / Rules and Regulations 5757

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of February

22, 2000.

Comments for inclusion in the Rules

Docket must be received on or before

March 8, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

16–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

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:

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: 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 A300 series

airplanes. The DGAC advises that,

during a routine maintenance check, a

horizontal crack of 35.6 inches was

detected in the surrounding panel above

the right mid-passenger door. The exact

cause of the cracking is unknown at this

time. The area of the crack is covered by

a sealant bead at the junction of two

skin panels and is not visible from the

outside. After the insulation blankets

were removed from the inside, the crack

was visually detected 1 inch below

stringer 11, and started 9 inches from

frame 29 and extended 6.7 inches aft

frame 30. Such cracking, if not detected

and corrected, could result in reduced

structural integrity of the fuselage

pressure vessel.

Explanation of Relevant Service

Information

Airbus has issued All Operators Telex

(AOT) A300–53A0352, dated January 4,

2000, which describes procedures for a

one-time ultrasonic inspection and

repetitive detailed visual inspections to

detect cracking of the longitudinal skin

splice above the mid-passenger door

panels below stringer 11 left- and righthand and between frames 28A and 30A,

and corrective actions, if necessary. The

corrective actions involve installing

either a temporary or permanent repair.

The temporary repair consists of stop

drilling all cracks and installing an

external doubler attached with rivets.

The temporary repair is to be replaced

with a permanent repair within 2,000

flight cycles. The permanent repair

consists of cutting out all cracked areas,

and installing an external doubler with

a milled step. The DGAC classified this

AOT as mandatory and issued French

airworthiness directive T2000–001–

300(B), Revision 1, dated January 7,

2000, in order to assure the continued

airworthiness of these airplanes in

France.

FAA’s Conclusions

This airplane model is manufactured

in France and is 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. 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 Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design registered in the United

States, this AD is being issued to detect

and correct cracking of the longitudinal

skin splice above the mid-passenger

door panels, which could result in

reduced structural integrity of the

fuselage pressure vessel. This AD

requires accomplishment of the actions

specified in the AOT described

previously, except as discussed below.

This AD also requires that operators

report results of all inspection findings

to Airbus.

Differences Between Rule and AOT

Operators should note that, unlike the

procedures described in the Airbus

AOT, this AD would not permit further

flight if cracks are detected. The FAA

has determined that, because of the

safety implications and consequences

associated with such cracking, any

cracks must be repaired or modified

prior to further flight.

Interim Action

This is considered to be interim

action. The inspection reports that are

required by this AD will enable the

manufacturer to obtain better insight

into the nature, cause, and extent of the

cracking, and eventually to develop

final action to address the unsafe

condition. Once final action has been

identified, the FAA may consider

further rulemaking.

Determination of Rule’s Effective Date

Since a situation exists that requires

the immediate adoption of this

regulation, it is found that notice and

opportunity for prior public comment

hereon are impracticable, and that good

cause exists for making this amendment

effective in less than 30 days.

Comments Invited

Although this action is in the form of

a final rule that involves requirements

affecting flight safety and, thus, was not

preceded by notice and an 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.

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–16–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

5758 Federal Register / Vol. 65, No. 25 / Monday, February 7, 2000 / Rules and Regulations

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.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and that it is not a ‘‘significant

regulatory action’’ under Executive

Order 12866. It has been determined

further that this action involves an

emergency regulation under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979). If it is

determined that this emergency

regulation otherwise would be

significant under DOT Regulatory

Policies and Procedures, a final

regulatory evaluation will be prepared

and placed in the Rules Docket. A copy

of it, if filed, 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:

2000–02–39 Airbus Industrie: Amendment

39–11557. Docket 2000–NM–16–AD.

Applicability: Model A300 series airplanes,

having serial numbers 1 through 156

inclusive; certificated in any category; except

those airplanes on which Airbus

Modification 2611 has been installed.

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

longitudinal skin splice above the midpassenger door panels, which could result in

reduced structural integrity of the fuselage

pressure vessel, accomplish the following:

Ultrasonic or Detailed Visual Inspection

(a) Within 14 days after the effective date

of this AD, accomplish the requirements of

either paragraph (a)(1) or (a)(2) of this AD, in

accordance with Airbus All Operators Telex

(AOT) A300–53A0352, dated January 4,

2000.

(1) Perform a one-time ultrasonic

inspection to detect cracking of the

longitudinal skin splice above the midpassenger door panels below stringer 11 (leftand right-hand) and between frames 28A and

30A.

(i) If no cracking is detected, no further

action is required by this AD.

(ii) If any cracking is detected, prior to

further flight, accomplish the requirements of

paragraph (b) of this AD.

(2) Perform a detailed visual inspection to

detect cracking of the longitudinal skin splice

above the mid-passenger door panels below

stringer 11 (left- and right-hand) and between

frames 28A and 30A.

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

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

Surface cleaning and elaborate access

procedures may be required.’’

(i) If no cracking is detected, accomplish

the requirements of paragraphs (a)(2)(i)(A)

and (a)(2)(i)(B) of this AD.

(A) Repeat the detailed visual inspection

thereafter at intervals not to exceed 80 flight

cycles; and

(B) Within 90 days after the effective date

of this AD, accomplish the requirements of

paragraph (a)(1) of this AD.

(ii) If any cracking is detected, prior to

further flight, accomplish the requirements of

paragraph (b) of this AD.

Corrective Actions

(b) For airplanes on which any cracking is

detected during any inspection required by

paragraph (a)(1) or (a)(2) of this AD, prior to

further flight, install either a temporary or

permanent repair, in accordance with Airbus

AOT A300–53A0352, dated January 4, 2000.

(1) If a temporary repair is installed, prior

to the accumulation of 2,000 flight cycles

after the installation of the temporary repair,

install the permanent repair.

(2) If a permanent repair is installed, no

further action is required by this AD.

Reporting Requirement

(c) Within 10 days after accomplishing the

initial inspection required by paragraph (a)(1)

or (a)(2) of this AD, and after all repetitive

inspections required by paragraph (a)(2)(i) of

this AD, as applicable, submit a report of the

inspection results (both positive and negative

findings) to: Mr. Rolland Filaquier—AI/SE–

A21, Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

Information collection requirements

contained in this regulation have been

approved by the Office of Management and

Budget (OMB) under the provisions of the

Paperwork Reduction Act of 1980 (44 U.S.C.

3501 et seq.) and have been assigned OMB

Control Number 2120–0056.

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, FAA,

Transport Airplane Directorate. 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) The actions shall be done in accordance

with Airbus All Operators Telex A300–

53A0352, dated January 4, 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 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 directive T2000–

001–300(B), Revision 1, dated January 7,

2000.

(g) This amendment becomes effective on

February 22, 2000.

Issued in Renton, Washington, on January

31, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–2467 Filed 2–4–00; 8:45 am]

BILLING CODE 4910–13–P