Airworthiness Directives; Airbus Model A300-600 and A310 Series Airplanes

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-82-AD]

RIN 2120-AA64

Airworthiness Directives; Airbus Model A300-600 and A310 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 A300-600 and A310

series airplanes. This proposal would require repetitive high frequency

eddy current (HFEC) inspections to detect cracking of the inner flange

of fuselage frame FR73A, between beams 5 and 7, and corrective actions,

if necessary. This proposal is prompted by issuance of mandatory

continuing airworthiness information by a foreign civil airworthiness

authority. The actions specified by the proposed AD are intended to

detect and correct fatigue cracking of the inner flange of fuselage

frame FR73A, which could result in reduced structural integrity of the

fuselage.

DATES: Comments must be received by February 4, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation

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

Attention: Rules Docket No. 99-NM-82-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

is 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-82-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-82-AD, 1601 Lind Avenue, SW., Renton, Washington

98055-4056.

Discussion

ich the following statement is made: ``Comments

to Docket Number 99-NM-82-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-82-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 A300-600 and A310 series

airplanes on which a certain fuselage frame FR73A modification has been

accomplished. The DGAC advises that, during the A330/A340 full-scale

fatigue test, a crack was found on the right-hand side of fuselage

frame FR73A between beams 5 and 6. The crack ran the full width of the

inner flange and extended 1.3 inches into the frame web. Such cracking,

if not detected and corrected, could result in reduced structural

integrity of the fuselage.

Identical Structures

Frame FR73A of Airbus Model A330/A340 series airplanes is identical

to frame FR73A of certain Model A300-600 and A310 series airplanes.

Therefore, Model A300-600 and A310 series airplanes are also subject to

the unsafe condition identified by this proposed AD.

Explanation of Relevant Service Information

Airbus has issued Service Bulletins A310-53-2107 (for Model A310

series airplanes) and A300-53-6116 (for Model A300-600 series

airplanes), both Revision 01, both dated July 2, 1999. These service

bulletins describe procedures for repetitive high frequency eddy

current (HFEC) inspections to detect cracking of the inner flange (left

and right sides) of fuselage frame FR73A, between beams 5 and 7; and

corrective actions, if necessary. The corrective actions involve rework

of frame FR73A or replacement with a new frame section between beams 5

and 7

both dated July 2, 1999. These service

bulletins describe procedures for repetitive high frequency eddy

current (HFEC) inspections to detect cracking of the inner flange (left

and right sides) of fuselage frame FR73A, between beams 5 and 7; and

corrective actions, if necessary. The corrective actions involve rework

of frame FR73A or replacement with a new frame section between beams 5

and 7. However, accomplishment of these actions would not eliminate the

need for repetitive HFEC inspections. Furthermore, the service

bulletins recommend that operators report all findings (both positive

and negative) to Airbus.

The DGAC classified the service bulletins as mandatory and issued

French airworthiness directive 1999-013-276(B), dated January 13, 1999,

in order to assure the continued airworthiness of these airplanes in

France.

FAA's Conclusions

These airplane models are manufactured in France and are 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 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 Airbus Service Bulletins A310-53-2107 and

A300-53-6116, described previously, except as discussed below.

The proposed AD also would require that operators report results of

inspection findings (both positive and negative) directly to Airbus.

lop on other airplanes of the same type design registered

in the United States, the proposed AD would require accomplishment of

the actions specified in Airbus Service Bulletins A310-53-2107 and

A300-53-6116, described previously, except as discussed below.

The proposed AD also would require that operators report results of

inspection findings (both positive and negative) directly to Airbus.

Differences Between Proposed Rule and Relevant Service Information

Operators should also note that, although both 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 the FAA or the DGAC (or its delegated agent).

Interim Action

This is considered to be interim action. The inspection reports

that would be required by this proposed 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 fully address the

unsafe condition. Once final action has been identified, the FAA may

consider further rulemaking.

Cost Impact

The FAA estimates that 198 airplanes of U.S. registry would be

affected by this proposed AD, that it would take approximately 1 work

hour per airplane to accomplish the proposed inspection, and that the

average labor rate is $60 per work hour. Based on these figures, the

cost impact of the proposed AD on U.S. operators is estimated to be

$11,880, or $60 per airplane, per inspection cycle.

The cost impact figure discussed above is based on assumptions that

no operator has yet accomplished any of the proposed requirements of

this AD action, and that no operator would accomplish those actions in

the future if this AD were not adopted.

Regulatory Impact

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 Industrie: Docket 99-NM-82-AD.

Applicability: Model A300-600 and A310 series airplanes,

certificated in any category, on which Airbus Modification 6925 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 (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 inner flange of

fuselage frame FR73A, which could result in reduced structural

integrity of the fuselage, accomplish the following:

HFEC Inspection

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 inner flange of

fuselage frame FR73A, which could result in reduced structural

integrity of the fuselage, accomplish the following:

HFEC Inspection

(a) Prior to the accumulation of 18,000 total flight cycles, or

within 3,000 flight cycles after the effective date of this AD,

whichever occurs later: Perform a high frequency eddy current (HFEC)

inspection to detect cracking of the inner flange (left and right

sides) of the rear fuselage frame FR73A, between beams 5 and 7, in

accordance with Airbus Service Bulletin A310-53-2107, Revision 01

(for Model A310 series airplanes), or A300-53-6116, Revision 01 (for

Model A300-600 series airplanes); both dated July 2, 1999; as

applicable.

(1) If no crack is detected, repeat the HFEC inspection

thereafter at intervals not to exceed 5,000 flight cycles.

(2) For any crack that is less than or equal to 0.20 inch (5.0

millimeters) in length: Prior to further flight, accomplish either

paragraph (a)(2)(i) or (a)(2)(ii) of this AD.

(i) Rework the frame in accordance with the applicable service

bulletin. Within 3,000 flight cycles after accomplishing the rework,

replace the fuselage frame FR73A between beams 5 and 7 with a new

frame section in accordance with the applicable service bulletin. Or

(ii) Replace the fuselage frame FR73A between beams 5 and 7 with

a new frame section, in accordance with the applicable service

bulletin.

(3) For any crack greater than 0.20 inch (5.0 millimeters) in

length: Prior to further flight, accomplish either paragraph

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

en beams 5 and 7 with a new

frame section in accordance with the applicable service bulletin. Or

(ii) Replace the fuselage frame FR73A between beams 5 and 7 with

a new frame section, in accordance with the applicable service

bulletin.

(3) For any crack greater than 0.20 inch (5.0 millimeters) in

length: Prior to further flight, accomplish either paragraph

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

(i) 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). Or

(ii) Replace the fuselage frame FR73A between beams 5 and 7 with

a new section, in accordance with the applicable service bulletin.

(b) Within 18,000 flight cycles after any replacement

accomplished in accordance with paragraph (a)(2)(i), (a)(2)(ii), or

(a)(3)(ii) of this AD: Repeat the inspection specified by paragraph

(a) of this AD. Thereafter, repeat the inspection at intervals not

to exceed 5,000 flight cycles.

(c) Submit a report of inspection findings (both positive and

negative) of any inspection required by this AD to Airbus Industrie,

Customer Services Directorate, 1 Rond Point Maurice Bellonte, 31707

Blagnac Cedex, France; at the applicable time specified in paragraph

(c)(1) or (c)(2) of this AD. The report must include the inspection

results, a description of any discrepancies found, the airplane

serial number, the age of the airplane since entry into service, and

the number of landings and flight hours on the airplane. 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.

(1) For airplanes on which the inspection required by paragraph

, and

the number of landings and flight hours on the airplane. 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.

(1) For airplanes on which the inspection required by paragraph

(a) of this AD is accomplished after the effective date of this AD:

Submit the report within 10 days after performing the inspection.

(2) For airplanes on which the inspection required by paragraph

(a) of this AD has been accomplished prior to the effective date of

this AD: Submit the report within 10 days after the effective date

of this AD.

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 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

(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.

Note 3: The subject of this AD is addressed in French

airworthiness directive 1999-013-276(B), dated January 13, 1999.

Issued in Renton, Washington, on December 29, 1999.

D.L. Riggin,

Acting Manager, Transport Airplane Directorate, Aircraft Certification

Service.

[FR Doc. 00-137 Filed 1-4-00; 8:45 am]

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