55524 Federal Register / Vol. 63, No. 200 / Friday, October 16, 1998 /Rules and Regulations

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 T98–376–

260 (B).

(h) This amendment becomes effective on

November 2, 1998.

Issued in Renton, Washington, on October

7, 1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–27480 Filed 10–15–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–341–AD; Amendment

39–10842; AD 98–21–34]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300, A310, and A300–600 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,

A310, and A300–600 series airplanes,

that requires repetitive inspections to

detect corrosion and cracks on the

bottom area of the wing skin, and

corrective action, if necessary. 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 corrosion and cracks

on the bottom area of the wing skin,

which could result in reduced structural

integrity of the airplane.

DATES: Effective November 20, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of November

20, 1998.

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 all Airbus Model

A300, A310, and A300–600 series

airplanes was published in the Federal

Register on March 24, 1998 (63 FR

14044). That action proposed to require

repetitive inspections to detect

corrosion and cracks on the bottom area

of the wing skin, and corrective action,

if necessary.

Comments

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 Clarify Certain Data in Table

3

The commenter (the manufacturer)

requests that the proposal be revised to

specify the correct value for a certain

inspection interval. The commenter

notes that the compliance time listed in

Table 3. of the proposed AD specifies

that the nondestructive testing (NDT)

high frequency eddy current (HFEC)

inspection interval for area ‘‘1, 2, 3a’’

should read ‘‘21,100 flight hours,’’

instead of ‘‘12,100 flight hours.’’

The FAA concurs. Based on a review

of the information provided by the

manufacturer, the FAA finds that, as

published, the proposed AD contains a

typographical error in Table 3. in the

‘‘NDT (HFEC) Interval’’ column for area

‘‘1, 2, 3a.’’ The FAA has revised Table

3. of the final rule to indicate the correct

inspection interval of 21,100 flight

hours.

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 49 Model

A300 and A310 series airplanes, and 51

Model A300–600 series airplanes, of

U.S. registry will be affected by this AD,

that it will take approximately 8 work

hours per airplane per inspection cycle

to accomplish the required actions, and

that the average labor rate is $60 per

work hour. Based on these figures, the

cost impact of the AD on U.S. operators

is estimated to be $48,000, or $480 per

airplane, per inspection cycle.

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.

Regulatory Impact

The regulations adopted herein will

not have substantial direct effects 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, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

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:
Federal Register / Vol. 63, No. 200 / Friday, October 16, 1998 /Rules and Regulations 55525

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:

98–21–34 Airbus Industrie: Amendment

39–10842. Docket 97–NM–341–AD.

Applicability: All Model A300, A310, and

A300–600 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 corrosion and cracks

on the bottom wing skin area, which could

result in reduced structural integrity of the

airplane, accomplish the following:

(a) At the time specified in paragraph

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

applicable: Except as required by paragraphs

(b) and (c) of this AD, perform an inspection

for corrosion and cracks on the bottom wing

skin area, and accomplish follow-on

corrective actions, in accordance with Airbus

Service Bulletin A300–57–0204, dated

December 4, 1995 (for Model A300 series

airplanes); A310–57–2061, dated December

4, 1995 (for Model A310 series airplanes); or

A300–57–6047, Revision 01, dated October

16, 1996, as revised by Change Notice 1.A.,

dated February 24, 1997 (for Model A300–

600 series airplanes); as applicable;

subsequently referred to in this AD as the

‘‘applicable’’ service bulletins. Thereafter,

repeat the inspection at intervals not to

exceed 5 years.

(1) For airplanes with 5 years or less since

date of manufacture: Prior to the

accumulation of 5 years since date of

manufacture or within 18 months after the

effective date of this AD, whichever occurs

later.

(2) For airplanes with more than 5 years,

but less than 15 years since date of

manufacture: Within 18 months after the

effective date of this AD.

(3) For airplanes with more than 15 years,

but less than 20 years since date of

manufacture: Within 12 months after the

effective date of this AD.

(4) For airplanes with more than 20 years

since date of manufacture: Within 6 months

after the effective date of this AD.

(b) If any corrosion or crack is found

during an inspection required by paragraph

(a) of this AD, and the applicable service

bulletin specifies to contact Airbus for an

appropriate action: Prior to further flight,

repair in accordance with a method approved

by the Manager, International Branch, ANM–

116, FAA, Transport Airplane Directorate.

(c) If any crack is found during an

inspection required by paragraph (a) of this

AD, and the applicable service bulletin

specifies to refer to Table B, Figure 4, of the

service bulletin to determine the fatigue

inspection threshold and interval: Use Table

1, 2, 3, 4, or 5, of this AD, as applicable, to

determine the fatigue inspection threshold

and interval in flight cycles (FC) or flight

hours (FH).

TABLE 1.—AIRBUS SERVICE BULLETIN A300–57–204 (MODEL A300 B2) FATIGUE INSPECTION

Area Threshold (FC or FH, whichever occurs first)

Detailed visual interval (FC or FH,

whichever occurs first)

NDT (HFEC) Interval (FC or FH,

whichever occurs first)

1, 2, 3a 1 ......................... 10,400 FC or 15,800 FH ................... 10,400 FC or 15,800 FH ................... 10,400 FC or 15,800 FH.

3b, 4a 2 ........................... 7,200 FC or 11,000 FH ..................... 2,500 FC or 3,800 FH ....................... 6,300 FC or 9,600 FH.

4b ................................... 10,400 FC or 15,800 FH ................... 10,400 FC or 15,800 FH ................... 10,400 FC or 15,800 FH.

5, 6 ................................. 9,900 FC or 15,100 FH ..................... 8,700 FC or 13,200 FH ..................... 9,900 FC or 15,100 FH.

7, 8 ................................. 6,600 FC or 10,000 FH ..................... 5,000 FC or 7,700 FH ....................... 6,400 FC or 9,700 FH.

1Area 3, as defined by Table B, Table 4, of SB A300–57–0204, has been split into areas 3a and 3b with a borderline between stiffener 43.2

and lattice flange 44 for Tables 1, 2, and 3 of this AD. 2Area 4, as defined by Table B, Table 4, of SB A300–57–0204, has been split into areas 4a and 4b with a borderline between lattice flange 44

for stiffener 44.1 for Tables 1, 2, and 3 of this AD.

TABLE 2.—AIRBUS SERVICE BULLETIN A300–57–204 (MODEL A300 B4–100) FATIGUE INSPECTION

Area Threshold (FC or FH, whichever occurs first)

Detailed visual interval (FC or FH,

whichever occurs first)

NDT (HFEC) interval (FC or FH,

whichever occurs first)

1, 2, 3a ........................... 9,500 FC or 15,600 FH ..................... 8,600 FC or 14,200 FH ..................... 9,500 FC or 15,600 FH.

3b, 4a ............................. 6,700 FC or 12,000 FH ..................... 2,000 FC or 3,300 FH ....................... 5,000 FC or 8,200 FH.

4b ................................... 9,500 FC or 15,600 FH ..................... 8,600 FC or 14,200 FH ..................... 9,500 FC or 15,600 FH.

5, 6 ................................. 8,200 FC or 13,400 FH ..................... 7,200 FC or 11,900 FH ..................... 8,200 FC or 13,400 FH.

7, 8 ................................. 4,600 FC or 7,600 FH ....................... 3,600 FC or 5,900 FH ....................... 4,500 FC or 7,400 FH.

TABLE 3.—AIRBUS SERVICE BULLETIN A300–57–204 (MODEL A300 B4–100) FATIGUE INSPECTION

Area Threshold (FC or FH, whichever occurs first)

Detailed visual interval (FC or FH,

whichever occurs first)

NDT (HFEC) interval (FC or FH,

whichever occurs first)

1, 2, 3a ........................... 9,900 FC or 21,600 FH ..................... 9,000 FC or 19,200 FH ..................... 9,900 FC or 21,100 FH.

3b, 4a ............................. 7,000 FC or 14,900 FH ..................... 2,100 FC or 4,500 FH ....................... 5,200 FC or 11,100 FH.

4b ................................... 9,900 FC or 21,100 FH ..................... 9,000 FC or 19,200 FH ..................... 9,900 FC or 21,100 FH.

5, 6 ................................. 8,500 FC or 18,100 FH ..................... 7,500 FC or 16,000 FH ..................... 8,500 FC or 18,100 FH.

7, 8 ................................. 4,800 FC or 10,200 FH ..................... 3,700 FC or 7,900 FH ....................... 4,700 FC or 10,000 FH.
55526 Federal Register / Vol. 63, No. 200 / Friday, October 16, 1998 /Rules and Regulations

TABLE 4.—AIRBUS SERVICE BULLETIN A330–57–2061 (MODEL A310 AND A310–300) FATIGUE INSPECTION

Area Threshold (FC or FH, whichever occurs first)

Detailed visual interval (FC or FH,

whichever occurs first)

NDT (HFEC) interval (FC or FH,

whichever occurs first)

1 ..................................... 12,800 FC or 36,600 FH ................... 10,500 FC or 29,900 FH ................... 12,800 FC or 36,600 FH.

2 ..................................... 5,700 FC or 16,300 FH ..................... 4,600 FC or 13,100 FH ..................... 5,700 FC or 16,300 FH.

3, 5 ................................. 5,100 FC or 14,700 FH ..................... 4,100 FC or 11,800 FH ..................... 5,100 FC or 14,700 FH.

4 ..................................... 4,500 FC or 12,800 FH ..................... 1,800 FC or 5,100 FH ....................... 4,500 FC or 12,800 FH.

6 ..................................... 19,400 FC or 55,300 FH ................... 16,500 FC or 47,000 FH ................... 19,400 FC or 55,300 FH.

7 ..................................... 16,300 FC or 46,500 FH ................... 13,800 FC or 39,500 FH ................... 16,300 FC or 46,500 FH.

TABLE 5.—AIRBUS SERVICE BULLETIN A300–57–6047 (MODEL A300–600) FATIGUE INSPECTION

Area Threshold (FC or FH, whichever occurs first)

Detailed visual interval (FC or FH,

whichever occurs first)

NDT (HFEC) interval (FC or FH,

whichever occurs first)

1, 2 ................................. 13,600 FC or 42,900 FH ................... 11,800 FC or 37,000 FH ................... 15,500 FC or 48,800 FH.

3 ..................................... 6,500 FC or 20,400 FH ..................... 5,800 FC or 18,400 FH ..................... 6,900 FC or 21,600 FH.

4, 6 ................................. 4,800 FC or 15,100 FH ..................... 4,500 FC or 14,200 FH ..................... 5,000 FC or 15,700 FH

5 ..................................... 2,100 FC or 6,500 FH ....................... 900 FC or 3,000 FH .......................... 2,100 FC or 6,500 FH.

7 ..................................... 5,700 FC or 18,100 FH ..................... 5,500 FC or 17,200 FH ..................... 6,300 FC or 19,800 FH.

8 ..................................... 2,400 FC or 7,400 FH ....................... 2,100 FC or 6,500 FH ....................... 2,400 FC or 7,400 FH.

(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.

(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.

(f) Except as provided by paragraphs (b) and (c) of this AD, the actions shall be done in accordance with the following Airbus

service bulletins, as applicable, which contain the specified effective pages:

Service bulletin referenced and date Page No.

Revision

level shown

on page

Date shown on page

A300–57–0204, December 4, 1995 ...................................................................................... 1–101 ........... Original ...... December 4, 1995.

A310–57–2061, December 4, 1995 ...................................................................................... 1–111 ........... Original ...... December 4, 1995.

A300–57–6047, October 16, 1996 ........................................................................................ 1–3, 29, 30 .. 01 ............... October 16, 1996.

4–29, 31–65 Original ...... January 4, 1996.

Change Notice 1.A., February 24, 1997, for Airbus Service Bulletin A300–57–6047, October 16, 1996.1, 2 ............... Original ...... February 24, 1997.

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 97–006–

210(B), dated January 2, 1997.

(g) This amendment becomes effective on

November 20, 1998.

Issued in Renton, Washington, on October

7, 1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–27479 Filed 10–15–98; 8:45 am]

BILLING CODE 4910–13–P