Airworthiness Directives; Airbus Model A330 and A340 Series Airplanes

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-184-AD; Amendment 39-11412; AD 99-23-16]

RIN 2120-AA64

Airworthiness Directives; Airbus Model A330 and A340 Series

Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD),

applicable to certain Airbus Model A330 and A340 series airplanes, that

requires repetitive detailed visual inspections to detect cracking of

the vertical flange of the inboard Z-stiffeners of the centerline panel

of the fuselage belly fairing; and corrective actions, if necessary.

This amendment also provides for optional terminating action for the

repetitive inspections. 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 vertical flange of the

inboard Z-stiffeners of the centerline panel of the fuselage belly

fairing, which could result in reduced structural integrity of the

belly fairing.

DATES: Effective December 17, 1999.

The incorporation by reference of certain publications listed in

the regulations is approved by the Director of the Federal Register as

of December 17, 1999.

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 A330 and A340

series airplanes was published in the Federal Register on September 10,

1999 (64 FR 49110). That action proposed to require repetitive detailed

visual inspections to detect cracking of the vertical flange of the

inboard Z-stiffeners of the centerline panel of the fuselage belly

fairing; and corrective actions, if necessary. That action also

proposed to provide for optional terminating action for the repetitive

inspections.

Comments

Interested persons have been afforded an opportunity to participate

in the making of this amendment. Due consideration has been given to

the comment received.

One commenter, an operator, states that it will have the

terminating modification incorporated prior to delivery of its

airplanes.

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 as proposed.

[[Page 61486]]

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 1 work hour to

accomplish the required inspection, at an average labor rate of $60 per

work hour. Based on these figures, the cost impact of this AD would be

$60 per airplane, per inspection cycle.

Should an operator elect to accomplish the optional terminating

action provided by this AD, it would require approximately 7 work hours

to accomplish the optional terminating action, at an average labor rate

of $60 per work hour. Required parts would cost approximately $2,350

per airplane. Based on these figures, the cost impact of the optional

terminating action is estimated to be $2,770 per airplane.

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:

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.

Sec. 39.13 [Amended]

2. Section 39.13 is amended by adding the following new

airworthiness directive:

99-23-16 Airbus Industrie: Amendment 39-11412. Docket 99-NM-184-AD.

Applicability: Model A330 and A340 series airplanes; except

those airplanes on which Airbus Modification 42605, or Airbus

Service Bulletin A330-53-3019 (for Model A330 series airplanes) or

A340-53-4028 (for Model A340 series airplanes) has 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 (c) 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 vertical flange of

the inboard Z-stiffeners of the centerline panel of the fuselage

belly fairing, which could result in reduced structural integrity of

the belly fairing, accomplish the following:

Repetitive Detailed Visual Inspections

(a) Prior to the accumulation of 5,500 total flight cycles, or

within 500 flight hours after the effective date of this AD,

whichever occurs later, perform a detailed visual inspection to

detect cracking of the vertical flange of the inboard Z-stiffeners

of the centerline panel of the fuselage belly fairing, in accordance

with Airbus Service Bulletin A330-53-3020 (for Model A330 series

airplanes) or A340-53-4029 (for Model A340 series airplanes); each

dated November 30, 1995; as applicable.

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 mirror, magnifying lenses, etc. may be used. Surface cleaning and

elaborate access procedures may be required.''

(1) If no cracking is detected, repeat the inspection thereafter

at intervals not to exceed 5,500 flight cycles, until the

requirements of paragraph (b) of this AD are accomplished.

Corrective Actions

(2) If any cracking is detected during any inspection required

by this AD, prior to further flight, modify the vertical flange of

both inboard Z-stiffeners of the centerline panel of the fuselage

belly fairing and re-inspect the modified area to determine if

cracking has been eliminated, in accordance with Airbus Service

Bulletin A330-53-3019 (for Model A330 series airplanes) or A340-53-

4028 (for Model A340 series airplanes); each dated November 30,

1995; as applicable.

(i) If all cracking is not eliminated after accomplishment of

the modification, prior to further flight, repair in accordance with

a method approved by either the Manager, International Branch, ANM-

116, FAA, Transport Airplane Directorate; or the Direction Generale

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.

(ii) If all cracking is eliminated after the accomplishment of

the modification, no further action is required by this AD.

Optional Terminating Action

(b) Modification of the vertical flange of both inboard Z-

stiffeners of the centerline panel of the fuselage belly fairing in

accordance with Airbus Service Bulletin A330-53-3019 (for Model A330

series airplanes) or A340-53-4028 (for Model A340 series airplanes);

each dated November 30, 1995; as applicable; constitutes terminating

action for the requirements of this AD.

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, 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 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

(d) Special flight permits may be issued in accordance with

sections 21.197 and 21.199

[[Page 61487]]

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 inspections and modification shall be done in accordance

with Airbus Service Bulletin A330-53-3020, dated November 30, 1995;

Airbus Service Bulletin A340-53-4029, dated November 30, 1995;

Airbus Service Bulletin A330-53-3019, dated November 30, 1995; and

Airbus Service Bulletin A340-53-4028, dated November 30, 1995; 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 4: The subject of this AD is addressed in French

airworthiness directives 96-056-029 (B) and 96-057-042 (B); each

dated March 13, 1996.

(f) This amendment becomes effective on December 17, 1999.

Issued in Renton, Washington, on November 3, 1999.

D.L. Riggin,

Acting Manager, Transport Airplane Directorate, Aircraft Certification

Service.

[FR Doc. 99-29327 Filed 11-10-99; 8:45 am]

BILLING CODE 4910-13-P