AD 2000-02-39

[Federal Register Volume 65, Number 25 (Monday, February 7, 2000)]
[Rules and Regulations]
[Pages 5756-5758]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-2467]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-16-AD; Amendment 39-11557; AD 2000-02-39]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 Series Airplanes

AGENCY:  Federal Aviation Administration, DOT.

ACTION:  Final rule; request for comments.

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SUMMARY:  This amendment adopts a new airworthiness directive (AD) that 
is applicable to certain Airbus Model A300 series airplanes. This 
action requires either a one-time ultrasonic inspection, or repetitive 
visual inspections and eventual ultrasonic inspection, to detect 
cracking of the longitudinal skin splice above the mid-passenger door 
panels, and corrective actions, if necessary. This amendment is 
prompted by issuance of mandatory continuing airworthiness information 
by a foreign civil airworthiness authority. The actions specified in 
this AD are intended to detect and correct cracking of the longitudinal 
skin splice above the mid-passenger door panels, which could result in 
reduced structural integrity of the fuselage pressure vessel.

DATES:  Effective February 22, 2000.

[[Page 5757]]

    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of February 22, 2000.
    Comments for inclusion in the Rules Docket must be received on or 
before March 8, 2000.

ADDRESSES:  Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-16-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056.
    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 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.

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:  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 
series airplanes. The DGAC advises that, during a routine maintenance 
check, a horizontal crack of 35.6 inches was detected in the 
surrounding panel above the right mid-passenger door. The exact cause 
of the cracking is unknown at this time. The area of the crack is 
covered by a sealant bead at the junction of two skin panels and is not 
visible from the outside. After the insulation blankets were removed 
from the inside, the crack was visually detected 1 inch below stringer 
11, and started 9 inches from frame 29 and extended 6.7 inches aft 
frame 30. Such cracking, if not detected and corrected, could result in 
reduced structural integrity of the fuselage pressure vessel.

Explanation of Relevant Service Information

    Airbus has issued All Operators Telex (AOT) A300-53A0352, dated 
January 4, 2000, which describes procedures for a one-time ultrasonic 
inspection and repetitive detailed visual inspections to detect 
cracking of the longitudinal skin splice above the mid-passenger door 
panels below stringer 11 left- and right-hand and between frames 28A 
and 30A, and corrective actions, if necessary. The corrective actions 
involve installing either a temporary or permanent repair. The 
temporary repair consists of stop drilling all cracks and installing an 
external doubler attached with rivets. The temporary repair is to be 
replaced with a permanent repair within 2,000 flight cycles. The 
permanent repair consists of cutting out all cracked areas, and 
installing an external doubler with a milled step. The DGAC classified 
this AOT as mandatory and issued French airworthiness directive T2000-
001-300(B), Revision 1, dated January 7, 2000, in order to assure the 
continued airworthiness of these airplanes in France.

FAA's Conclusions

    This airplane model is manufactured in France and is 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 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, this AD is being issued to detect and correct 
cracking of the longitudinal skin splice above the mid-passenger door 
panels, which could result in reduced structural integrity of the 
fuselage pressure vessel. This AD requires accomplishment of the 
actions specified in the AOT described previously, except as discussed 
below. This AD also requires that operators report results of all 
inspection findings to Airbus.

Differences Between Rule and AOT

    Operators should note that, unlike the procedures described in the 
Airbus AOT, this AD would not permit further flight if cracks are 
detected. The FAA has determined that, because of the safety 
implications and consequences associated with such cracking, any cracks 
must be repaired or modified prior to further flight.

Interim Action

    This is considered to be interim action. The inspection reports 
that are required by this 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 address the unsafe condition. 
Once final action has been identified, the FAA may consider further 
rulemaking.

Determination of Rule's Effective Date

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this 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 under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the 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 that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2000-NM-16-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    The regulations adopted herein will not have a substantial direct 
effect on the States, on the relationship between

[[Page 5758]]

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 final rule does not have federalism 
implications under Executive Order 13132.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, 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:

2000-02-39  Airbus Industrie: Amendment 39-11557. Docket 2000-NM-16-
AD.

    Applicability: Model A300 series airplanes, having serial 
numbers 1 through 156 inclusive; certificated in any category; 
except those airplanes on which Airbus Modification 2611 has been 
installed.

    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 cracking of the longitudinal skin splice 
above the mid-passenger door panels, which could result in reduced 
structural integrity of the fuselage pressure vessel, accomplish the 
following:

Ultrasonic or Detailed Visual Inspection

    (a) Within 14 days after the effective date of this AD, 
accomplish the requirements of either paragraph (a)(1) or (a)(2) of 
this AD, in accordance with Airbus All Operators Telex (AOT) A300-
53A0352, dated January 4, 2000.
    (1) Perform a one-time ultrasonic inspection to detect cracking 
of the longitudinal skin splice above the mid-passenger door panels 
below stringer 11 (left-and right-hand) and between frames 28A and 
30A.
    (i) If no cracking is detected, no further action is required by 
this AD.
    (ii) If any cracking is detected, prior to further flight, 
accomplish the requirements of paragraph (b) of this AD.
    (2) Perform a detailed visual inspection to detect cracking of 
the longitudinal skin splice above the mid-passenger door panels 
below stringer 11 (left- and right-hand) and between frames 28A and 
30A.

    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 mirrors, magnifying lenses, etc., may be used. Surface cleaning 
and elaborate access procedures may be required.''

    (i) If no cracking is detected, accomplish the requirements of 
paragraphs (a)(2)(i)(A) and (a)(2)(i)(B) of this AD.
    (A) Repeat the detailed visual inspection thereafter at 
intervals not to exceed 80 flight cycles; and
    (B) Within 90 days after the effective date of this AD, 
accomplish the requirements of paragraph (a)(1) of this AD.
    (ii) If any cracking is detected, prior to further flight, 
accomplish the requirements of paragraph (b) of this AD.

Corrective Actions

    (b) For airplanes on which any cracking is detected during any 
inspection required by paragraph (a)(1) or (a)(2) of this AD, prior 
to further flight, install either a temporary or permanent repair, 
in accordance with Airbus AOT A300-53A0352, dated January 4, 2000.
    (1) If a temporary repair is installed, prior to the 
accumulation of 2,000 flight cycles after the installation of the 
temporary repair, install the permanent repair.
    (2) If a permanent repair is installed, no further action is 
required by this AD.

Reporting Requirement

    (c) Within 10 days after accomplishing the initial inspection 
required by paragraph (a)(1) or (a)(2) of this AD, and after all 
repetitive inspections required by paragraph (a)(2)(i) of this AD, 
as applicable, submit a report of the inspection results (both 
positive and negative findings) to: Mr. Rolland Filaquier--AI/SE-
A21, Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France. 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.

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 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

    (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.

Incorporation by Reference

    (f) The actions shall be done in accordance with Airbus All 
Operators Telex A300-53A0352, dated January 4, 2000. 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 directive T2000-001-300(B), Revision 1, dated January 
7, 2000.

    (g) This amendment becomes effective on February 22, 2000.

    Issued in Renton, Washington, on January 31, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-2467 Filed 2-4-00; 8:45 am]
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