02-201. Airworthiness Directives; Airbus Model A300 B2, A300 B4, A300 B4-600, and A300 B4-600R Series Airplanes; and Model A300 F4-605R Airplanes

AGENCY:

Federal Aviation Administration, DOT.

ACTION:

Supplemental notice of proposed rulemaking; reopening of comment period.

SUMMARY:

This document revises an earlier proposed airworthiness directive (AD), applicable to all Model A300 B2, A300 B4, A300 B4-600, and A300 B4-600R series airplanes, that would have required repetitive inspections for cracking of certain fittings, corrective action if necessary, and, for certain airplanes, a modification; and would have provided for optional terminating action for the repetitive inspections. This new action revises the proposed rule by including additional airplanes in the applicability. The actions specified by this new proposed AD are intended to detect and correct propagation of cracks on the frame 40 aft fittings due to local stress concentrations at the upper flange runout of frame 40, which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.

DATES:

Comments must be received by January 29, 2002.

ADDRESSES:

Submit comments in triplicate to the Federal Aviation Administration (FAA), Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 99-NM-86-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. Comments may be submitted via fax to [phone]. Comments may also be sent via the Internet using the following address: [e-mail]. Comments sent via fax or the Internet must contain “Docket No. 99-NM-86-AD” in the subject line and need not be submitted in triplicate. Comments sent via the Internet as attached electronic files must be formatted in Microsoft Word 97 for Windows or ASCII text.

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:

Dan Rodina, Aerospace Engineer, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone [phone]; fax [phone].

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 action may be changed in light of the comments received.

Submit comments using the following format:

• Organize comments issue-by-issue. For example, discuss a request to change the compliance time and a request to change the service bulletin reference as two separate issues.
• For each issue, state what specific change to the proposed AD is being requested.
• Include justification (e.g., reasons or data) for each request.

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 action must submit a self-addressed, stamped postcard on which the following statement is made: “Comments to Docket Number 99-NM-86-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-86-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056.

Discussion

A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to add an airworthiness directive (AD), applicable to all Model A300 B2, A300 B4, A300 B4-600, and A300 B4-600R series airplanes, was published as a supplemental notice of proposed rulemaking (NPRM) in the Federal Register on August 22, 2001 (66 FR 44089). That supplemental NPRM would have required repetitive inspections for cracking of certain fittings, corrective action if necessary, and, for certain airplanes, a modification; and would have provided for optional terminating action for the repetitive inspections. That supplemental NPRM was prompted by reports of cracked frame 40 aft fittings at stringer 33 on the left and right sides of the fuselage. The cracking has been attributed to local stress concentration at the upper flange runout of frame 40. That condition, if not corrected, could result in reduced structural integrity of the airplane.

Actions Since Issuance of Previous Proposal

Due consideration has been given to the comments received in response to the first supplemental NPRM.

Support for the Proposal

One commenter, an operator, generally supports the proposal. The commenter reports that the proposed actions, including the optional terminating action, have already been accomplished on most of its airplanes. The commenter also provides the cost of accomplishing the work on its fleet.

Request to Revise Applicability

One commenter, the manufacturer, requests that the applicability of the first supplemental NPRM be revised to include all Airbus Model A300 F4-605R airplanes. This commenter had earlier requested, in response to the original NPRM, that Model A300 F4-622R airplanes be removed from the applicability of the original NPRM. However, the commenter notes that Model A300 F4-605R airplanes were also removed from the applicability, although they are subject to the unsafe condition and should be included.

The FAA concurs, for the reasons identified by the commenter. Model A300 F4-605R airplanes had been inadvertently omitted from the applicability. The applicability section of this second supplemental NPRM has been revised accordingly.

Conclusion

Since this change expands the scope of the originally proposed rule, the FAA has determined that it is necessary to reopen the comment period to provide additional opportunity for public comment.

Cost Impact

The FAA estimates that 70 airplanes of U.S. registry would be affected by this second supplemental NPRM.

For affected airplanes, it would take approximately 92 work hours per airplane to accomplish the proposed modification, at an average labor rate of $60 per work hour. Required parts would cost as much as $874 per airplane. Based on these figures, the cost impact of the proposed modification is estimated to be as much as $6,394 per airplane.

It would take approximately 10 work hours per airplane to accomplish the proposed inspection, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the proposed inspection on U.S. operators is estimated to be $42,000, or $600 per airplane, per inspection cycle.

The cost impact figures discussed above are 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. The cost impact figures discussed in AD rulemaking actions represent only the time necessary to perform the specific actions actually required by the AD. These figures typically do not include incidental costs, such as planning time, time required to gain access and close up, or time necessitated by other administrative actions.

Regulatory Impact

The regulations proposed herein would not have a substantial direct effect 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, it is determined that this proposal would not have federalism implications under Executive Order 13132.

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
• Aircraft
• 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.

§ 39.13

[Amended]

2. Section 39.13 is amended by adding the following new airworthiness directive:

Airbus Industrie: Docket 99-NM-86-AD.

Applicability: All Model A300 B2, A300 B4, A300 B4-600, and A300 B4-600R series airplanes; and Model A300 F4-605R 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 (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 propagation of cracks on the frame 40 aft fittings due to local stress concentrations at the upper flange runout of frame 40, which could result in reduced structural integrity of the airplane, accomplish the following:

Modification

(a) For airplanes on which Airbus Modification 10430 has not been done before the effective date of this AD: Concurrently with the inspection required by paragraph (b) of this AD, modify the profile of frame 40 aft fittings per the service information specified in Table 1, as follows:

Table 1.—Service Information

For model—	Do the actions in accordance with either—	Of Airbus Service Bulletin—	Dated—
(1) A300 B2 and A300 B4 series airplanes	(i) Revision 01 or	A300-53-0296	Sept. 30, 1998.
	(ii) Revision 02	A300-53-0296	May 12, 1999.
(2) A300 B4-600 and A300 B4-600R series airplanes and Model A300 F4-605R airplanes	(i) Revision 01 or	A300-53-6048	Sept. 30, 1998.
	(ii) Revision 03	A300-53-6048	Feb. 21, 2000.

Note 2:

For Model A300 B4-600 and A300 B4-600R series airplanes and Model A300 F4-605R airplanes: Actions performed in accordance with Airbus Service Bulletin A300-53-6048, dated January 16, 1996; or Revision 02, dated May 12, 1999, are acceptable for compliance with the applicable requirements of this AD.

Note 3:

Airbus Service Bulletin A300-53-6048 refers to Airbus Service Bulletin A300-53-6063 as an additional source of service information for accomplishment of certain repairs.

Inspection

(b) For all airplanes, inspect the airplane per Table 2, as follows:

Table 2.—Inspection Requirements

Requirements	Description
(1) Area to inspect	The frame 40 AFT fitting.
(2) Type of inspection	Nondestructive test (NDT).
(3) Compliance time	As specified by paragraph (c) of this AD.
(4) Discrepancies to detect	Cracking.
(5) Service information	Inspect in accordance with the applicable service bulletin listed in Table 1 of this AD.
(6) Follow-on actions if you find no cracking	Repeat the inspection thereafter at the applicable interval specified by Table 3 of this AD.
(7) Corrective actions if you find cracking	Do the specified actions by paragraph (d) of this AD.
(8) Terminating action	The modification specified by paragraph (e) of this AD terminates the requirements of this AD.

Note 4:

An NDT per Part 6 53-15-30 procedure C of the NDT manual is also acceptable for compliance with the requirements of paragraph (b) of this AD.

(c) Perform the inspection required by paragraph (b) of this AD per the schedule in Table 3 of this AD. For airplanes on which this inspection has been accomplished before the effective date of this AD, the initial compliance time may be extended by the repetitive interval following the date the inspection was accomplished. Table 3 follows:

Table 3.—Compliance Times for Inspection

For model—	If the total flight cycles accumulated on the airplane as of the effective date of this AD is—	Then inspect—	And repeat the inspection at least every—
(1) A300 B4-600 and A300 B4-600R series airplanes and Model A300 F4-605R airplanes, past-Modification 10430	(i) Fewer than 6,200	Before the airplane accumulates 7,700 total flight cycles or 17,710 total flight hours, whichever occurs first	7,500 flight cycles or 17,250 flight hours, whichever occurs first.
	(ii) At least 6,200 and fewer than 9,700	Within 1,500 flight cycles or 3,450 flight hours after the effective date of this AD, whichever occurs first	7,500 flight cycles or 17,250 flight hours, whichever occurs first.
	(iii) At least 9,700	Within 750 flight cycles or 1,725 flight hours after the effective date of this AD, whichever occurs first	7,500 flight cycles or 17,250 flight hours, whichever occurs first.
(2) A300 B4-600 and A300 B4-600R series airplanes and Model A300 F4-605R airplanes, pre-Modification 10430	(i) Fewer than 19,600	Before the airplane accumulates 21,100 total flight cycles or 48,530 total flight hours, whichever occurs first	7,500 flight cycles or 17,250 flight hours, whichever occurs first.
	(ii) At least 19,600 and fewer than 23,100 9,700	Within 1,500 flight cycles or 3,450 flight hours after the effective date of this AD, whichever occurs first	7,500 flight cycles or 17,250 flight hours, whichever occurs first.
	(iii) At least 23,100	Within 750 flight cycles or 1,725 flight hours after the effective date of this AD, whichever occurs first	7,500 flight cycles or 17,250 flight hours, whichever occurs first.
(3) A300 B2 series airplanes	(i) Fewer than 12,000	Before the airplane accumulates 14,000 total flight cycles or 15,120 total flight hours, whichever occurs first	5,500 flight cycles or 5,940 flight hours, whichever occurs first.
	(ii) At least 12,000 and fewer than 17,000	Within 2,000 flight cycles or 2,160 flight hours after the effective date of this AD, whichever occurs first	5,500 flight cycles or 5,940 flight hours, whichever occurs first.
	(iii) At least 17,000	Within 1,000 flight cycles or 1,080 flight hours after the effective date of this AD, whichever occurs first	5,500 flight cycles or 5,940 flight hours, whichever occurs first.
(4) A300 B4-100 series airplanes	(i) Fewer than 9,500	Before the airplane accumulates 11,500 total flight cycles or 15,295 total flight hours, whichever occurs first	4,500 flight cycles or 5,985 flight hours, whichever occurs first.
	(ii) At least 9,500 and fewer than 14,500	Within 2,000 flight cycles or 2,660 flight hours after the effective date of this AD, whichever occurs first	4,500 flight cycles or 5,985 flight hours, whichever occurs first.
	(iii) At least 14,500	Within 1,000 flight cycles or 1,330 flight hours after the effective date of this AD, whichever occurs first	4,500 flight cycles or 5,985 flight hours, whichever occurs first.
(5) A300 B4-200 series airplanes	(i) Fewer than 8,500	Before the airplane accumulates 10,500 total flight cycles or 21,840 total flight hours, whichever occurs first	4,000 flight cycles or 8,320 flight hours, whichever occurs first.
	(ii) At least 8,500 and fewer than 13,500	Within 2,000 flight cycles or 4,160 flight hours after the effective date of this AD, whichever occurs first	4,000 flight cycles or 8,320 flight hours, whichever occurs first.
	(iii) At least 13,500	Within 1,000 flight cycles or 2,080 flight hours after the effective date of this AD, whichever occurs first	4,000 flight cycles or 8,320 flight hours, whichever occurs first.

Note 5:

An NDT inspection is also required by AD 98-25-07, amendment 39-10933, to be repetitively performed on Model A300 B4-600 and A300 B4-600R series airplanes and Model A300 F4-605R airplanes on which Airbus Modification 10453 has not been installed. For those airplanes, if the inspection is done within the applicable compliance time specified by paragraph (c) of this AD, the threshold for the initial inspection of paragraph (b) of this AD may be extended by 1,500 flight cycles.

Corrective Actions

(d) If any cracking is found during any inspection required by paragraph (b) of this AD: Except as required by paragraph (f) of this AD, prior to further flight, perform all applicable corrective actions in accordance with the applicable service bulletin identified in Table 1 of this AD.

Terminating Action

(e) Accomplishment of the applicable modification in accordance with the applicable service bulletin specified by paragraph (e)(1) or (e)(2) of this AD terminates the requirements of this AD.

(1) For Model A300 B4-600 and A300 B4-600R series airplanes: In accordance with Airbus Service Bulletin A300-57-6053, Revision 1, dated October 31, 1995; or Revision 02, dated June 2, 1999.

(2) For Model A300 B2 and A300 B4 series airplanes: In accordance with Airbus Service Bulletin A300-53-0297, Revision 2, dated October 31, 1995.

Exception to Service Bulletin Instructions

(f) During any inspection required by this AD, if the service bulletin specifies to contact the manufacturer for an appropriate action: Prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Direction Générale de l'Aviation Civile (DGAC) (or its delegated agent).

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 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 7:

The subject of this AD is addressed in French airworthiness directive 1998-481-270(B) R1, dated July 12, 2000.

Issued in Renton, Washington, on December 28, 2001.

Vi L. Lipski,

Manager, Transport Airplane Directorate, Aircraft Certification Service.