Airworthiness Directives; Airbus Model A330 and A340 Series Airplanes

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-241-AD]

RIN 2120-AA64

Airworthiness Directives; Airbus Model A330 and A340 Series

Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness

directive (AD) that is applicable to certain Airbus Model A330 and A340

series airplanes. This proposal would require repetitive inspections to

detect cracking of the fuselage skin in the area of the VHF2 antenna,

repair, if necessary. This proposal also would provide for optional

terminating action for the repetitive inspections. This proposal is

prompted by issuance of mandatory continuing airworthiness

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information by a foreign civil airworthiness authority. The actions

specified by the proposed AD are intended to detect and correct such

cracking, which could result in cabin depressurization of the airplane.

DATES: Comments must be received by January 31, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation

Administration (FAA), Transport Airplane Directorate, ANM-114,

Attention: Rules Docket No. 99-NM-241-AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055-4056. Comments may be inspected at this

location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except

Federal holidays.

The service information referenced in the proposed rule 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.

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:

Comments Invited

Interested persons are invited to participate in the making of the

proposed 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 above. All

communications received on or before the closing date for comments,

specified above, will be considered before taking action on the

proposed rule. The proposals contained in this notice may be changed in

light of the comments received.

Comments are specifically invited on the overall regulatory,

economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with

the substance of this proposal will be filed in the Rules Docket.

Commenters wishing the FAA to acknowledge receipt of their comments

submitted in response to this notice must submit a self-addressed,

stamped postcard on which the following statement is made: ``Comments

to Docket Number 99-NM-241-AD.'' The postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this NPRM by submitting a request

to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules

Docket No.99-NM-241-AD, 1601 Lind Avenue, SW., Renton, Washington

98055-4056.

Discussion

The Direction Generale 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 A330 and A340 series

airplanes. The DGAC advises that cracks have been found in the fuselage

skin aft of frame 54, between the airplane centerline and stringer 56R

in the area of the VHF2 antenna. The cracks were caused by fatigue

induced by the vibration of the VHF2 antenna during flight. This

antenna is installed on both Model A330 and A340 series airplanes.

Operators have reported 30 such occurrences on Model A330 and A340

series airplanes. Such cracking could result in cabin depressurization

of the airplane.

Explanation of Relevant Service Information

Airbus has issued Service Bulletin A330-53-3094, Revision 02, dated

May 28, 1998 (for Model A330 series airplanes), and Service Bulletin

A340-53-4105, Revision 02, dated May 25, 1998 (for Model A340 series

airplanes); which provide instructions for repetitive HFEC inspections

to detect cracks of the fuselage skin aft of frame 54, between the

airplane centerline and stringer 56R in the area of the VHF2 antenna,

and an interim repair procedure if cracks are found. Accomplishment of

the interim repair will stop further crack propagation until a

permanent repair can be accomplished. The interim repair consists of

cutting out the cracked portion of the fuselage skin, and installing a

filler plate in the skin cutout, two doublers, and shims. The DGAC

classified these service bulletins as mandatory and issued French

airworthiness directives 1998-192-071(B), Revision 01 (for Model A330

series airplanes) and 1998-193-089(B), Revision 01 (for Model A340

series airplanes), both dated March 24, 1999, in order to assure the

continued airworthiness of these airplanes in France.

Airbus has also issued Service Bulletin A330-53-3097, Revision 01,

dated May 21, 1999 (for Model A330 series airplanes), and Service

Bulletin A340-53-4108, Revision 01, dated May 21, 1999 (for Model A340

series airplanes); which provide terminating action for the repetitive

inspections. The terminating action consists of a modification to

reinforce the fuselage structure in the area of the VHF2 antenna. These

service bulletins were approved by the DGAC.

FAA's Conclusions

These airplane models are manufactured in France and are type

certificated for operation in the United States under the provisions of

Sec. 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 Proposed 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, the proposed AD would require accomplishment of

the actions specified in the service bulletins described previously,

except as discussed below. This proposed AD also would provide for an

interim repair, which if accomplished, would extend the interval for

the repetitive inspections. This proposed AD also would provide for

optional terminating action for the repetitive inspections.

Operators should note that, to be consistent with the findings of

the DGAC, the FAA has determined that the repetitive inspections

proposed by this AD can be allowed to continue in lieu of

accomplishment of a terminating action specified in the service

bulletins described previously. In making this determination, the FAA

considers that, in this case, long-term continued operational safety

will be adequately assured by accomplishing the repetitive inspections

to detect cracking before it represents a hazard to the airplane.

Differences Between Proposed Rule and Service Bulletins

Operators should note that, unlike the procedures described in

Airbus Service Bulletins A330-53-3094 and Service

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Bulletin A340-53-4105, this proposed AD would not permit further flight

if cracks are detected in the fuselage skin. The service bulletins

allow for a temporary repair to be applied to cracks below a certain

size, consisting of stop drilling the crack tip, until the interim

repair can be accomplished. The FAA has determined that, because of the

safety implications and consequences associated with such cracking, any

subject fuselage skin that is found to be cracked must be repaired

either with the interim repair or in accordance with a method approved

by the FAA (as applicable) prior to further flight.

In addition, although the service bulletins specify that the

manufacturer may be contacted for disposition of certain repair

conditions, this proposal would require the repair of those conditions

to be accomplished in accordance with a method approved by either the

FAA or the DGAC (or its delegated agent). In light of the type of

repair that would be required to address the identified unsafe

condition, and in consonance with existing bilateral airworthiness

agreements, the FAA has determined that, for this proposed AD, a repair

approved by either the FAA or the DGAC would be acceptable for

compliance with this proposed AD.

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 6 work hours to

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

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

be $360 per airplane, per inspection cycle.

Should an operator elect to accomplish the optional terminating

action rather than continue the repetitive inspections, it would take

approximately 112 work hours per airplane to accomplish the

modification, at an average labor rate of $60 per work hour. Based on

these figures, the cost impact of this optional terminating action is

estimated to be $6,720 per airplane.

Regulatory Impact

The regulations proposed herein would 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

proposal would not have sufficient federalism implications to warrant

the preparation of a Federalism Assessment.

For the reasons discussed above, I certify that this proposed

regulation (1) is not a ``significant regulatory action'' under

Executive Order 12866; (2) is not a ``significant rule'' under the DOT

Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);

and (3) if promulgated, 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 copy of the draft

regulatory evaluation prepared for this action is contained in the

Rules Docket. A copy of it may be obtained by contacting the Rules

Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Airplane, Aviation safety, Safety.

The Proposed Amendment

Accordingly, pursuant to the authority delegated to me by the

Administrator, the Federal Aviation Administration proposes to amend

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:

Airbus: Docket 99-NM-241-AD.

Applicability: Model A330 and A340 series airplanes,

certificated in any category; except those on which Airbus

production modification 46025 is installed or on which Airbus

Service Bulletin A330-53-3097, Revision 01, dated May 21, 1999 (for

Model A330 series airplanes), or Service Bulletin A340-53-4108,

Revision 01, dated May 21, 1999 (for Model A340 series airplanes),

has been accomplished.

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 (g) 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 fuselage skin in the area

of the VHF2 antenna, which could result in cabin depressurization of

the airplane, accomplish the following:

Detailed Visual Inspection

(a) At the latest of the times specified in paragraphs (a)(1),

(a)(2), (a)(3), and (a)(4) of this AD, as applicable: Perform a

detailed visual inspection (without removal of the VHF2 antenna) of

the fuselage skin aft of frame 54, between the airplane centerline

and stringer 56R in the area of the VHF2 antenna to detect cracks,

in accordance with Airbus Service Bulletin A330-53-3094, Revision

02, dated May 28, 1998 (for Model A330 series airplanes), or Service

Bulletin A340-53-4105, Revision 02, dated May 25, 1998 (for Model

A340 series airplanes) (hereinafter referred to as the applicable

service bulletin). Thereafter, if no cracks are detected, repeat the

detailed visual inspection every 36 flight hours until

accomplishment of the high frequency eddy current (HFEC) inspection

required by paragraph (b) of this AD.

(1) Prior to the accumulation of 900 total flight hours.

(2) Within 1,250 flight hours since accomplishment of the

interim repair specified by paragraph 2.C.(4) of the applicable

service bulletin, if the interim repair has been accomplished prior

to the effective date of this AD.

(3) Within 300 flight hours since the most recent HFEC

inspection accomplished in accordance with the applicable service

bulletin, if the most recent HFEC inspection has been accomplished

prior to the effective date of this AD.

(4) Within 36 flight hours after the effective date of this AD.

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.''

High Frequency Eddy Current Inspection

(b) Perform a high frequency eddy current (HFEC) inspection to

detect cracks of the fuselage skin aft of frame 54, between the

airplane centerline and stringer 56R in the

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area of the VHF2 antenna, in accordance with the applicable service

bulletin, at the applicable time specified by paragraph (b)(1) or

(b)(2) of this AD. Accomplishment of this inspection terminates the

requirements of paragraph (a) of this AD.

(1) For airplanes on which the interim repair specified by

paragraph 2.C.(4) of the applicable service bulletin has not been

accomplished: Prior to the accumulation of 900 total flight hours on

the airplane, or within 500 flight hours after the effective date of

this AD, whichever occurs later. Thereafter, accomplish the follow-

on actions of paragraph (c) or (d) of this AD, as applicable.

(2) For airplanes on which the interim repair specified by

paragraph 2.C.(4) of the applicable service bulletin has been

accomplished: Within 1,250 flight hours after accomplishment of the

interim repair, or within 500 flight hours after the effective date

of this AD, whichever occurs later.

Repetitive Inspections

(c) If no crack is detected during the HFEC inspection required

by paragraph (b) of this AD, accomplish the repetitive inspections

required by paragraph (c)(1) or (c)(2) of this AD, as applicable.

(1) For airplanes on which the interim repair specified by

paragraph 2.C.(4) of the applicable service bulletin has not been

accomplished, accomplish the actions specified by paragraphs

(c)(1)(i) and (c)(1)(ii) of this AD.

(i) Repeat the HFEC inspection specified by paragraph (b) at

intervals not to exceed 500 flight hours.

(ii) Within 300 flight hours after each HFEC inspection required

by this AD: Perform a detailed visual inspection (without removal of

the VHF2 antenna) of the fuselage skin aft of frame 54, between the

airplane centerline and stringer 56R in the area of the VHF2 antenna

to detect cracks, in accordance with the applicable service

bulletin. Thereafter, if no cracks are detected, repeat the detailed

visual inspection every 36 flight hours until accomplishment of the

next HFEC inspection required by paragraph (c)(1)(i) of this AD.

(2) For airplanes on which the interim repair specified by

paragraph 2.C.(4) of the applicable service bulletin has been

accomplished, repeat the HFEC inspection specified by paragraph (b)

of this AD at intervals not to exceed 1,250 flight hours.

Corrective Actions

(d) If any crack is detected during any inspection required by

paragraph (a), (b), or (c) of this AD, and the interim repair

specified by paragraph 2.C.(4) of the applicable service bulletin

has not been accomplished: Prior to further flight, accomplish the

actions specified by paragraph (d)(1) or (d)(2) of this AD, as

applicable.

(1) If only one crack is detected and that crack is 9.45 inches

or less, and is within the limits specified by the applicable

service bulletin: Install the interim repair specified in paragraph

2.C.(4) of the applicable service bulletin. Thereafter, repeat the

HFEC inspection specified by paragraph (b) of this AD at intervals

not to exceed 1,250 flight hours.

Note 3: The interim repair referenced by this AD consists of

cutting out the cracked portion of the fuselage skin, and installing

a filler plate in the skin cutout, two doublers, and shims, as

described in paragraph 2.C.(4) of the applicable service bulletin.

Note 4: Accomplishment of the interim repair in accordance with

paragraph 4.3 of Airbus Industrie All Operator Telex (AOT) 53-10,

dated September 24, 1997, is acceptable for compliance with the

requirements of paragraph (d)(1) of this AD.

(2) If any crack is detected that is longer than 9.45 inches, or

is outside the limits specified by the service bulletin, or if more

than one crack is detected: Repair in accordance with a method

approved by 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.

(e) If any crack is detected during any inspection required by

paragraph (a), (b), or (c) of this AD and the interim repair

specified by paragraph 2.C.(4) of the applicable service bulletin

has been accomplished: Prior to further flight, repair 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.

(f) Accomplishment of the modification as described in Airbus

Service Bulletin A330-53-3097, Revision 01, dated May 21, 1999 (for

Model A330 series airplanes), or Service Bulletin A340-53-4108,

Revision 01, dated May 21, 1999 (for Model A340 series airplanes),

terminates the repetitive inspections required by paragraphs (a),

(b), and (c) of this AD.

Note 5: Accomplishment of Airbus production modification 46025,

or the modification as described in Airbus Service Bulletin A330-53-

3097, dated July 29, 1998 (for Model A330 series airplanes), or

Service Bulletin A340-53-4108, dated July 31, 1998 (for Model A340

series airplanes), also constitutes terminating action for the

repetitive inspections required by paragraphs (a), (b), and (c) of

this AD.

Alternative Methods of Compliance

(g) 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 6: 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

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

Secs. 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.

Note 7: The subject of this AD is addressed in French

airworthiness directives 1998-192-071(B)R1 (for Model A330 series

airplanes) and 1998-193-089(B)R1 (for Model A340 series airplanes),

both dated March 24, 1999.

Issued in Renton, Washington, on December 23, 1999.

Vi L. Lipski,

Acting Manager, Transport Airplane Directorate, Airplane Certification

Service.

[FR Doc. 99-33950 Filed 12-29-99; 8:45 am]

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