[Federal Register Volume 63, Number 147 (Friday, July 31, 1998)]
[Proposed Rules]
[Pages 40850-40852]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-20437]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-169-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 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 A300 series 
airplanes. This proposal would require repetitive inspections to detect 
corrosion on the fuselage skin panels that surround the emergency exits 
immediately aft of the wing; and follow-on 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 corrosion on the fuselage skin panels that surround 
the emergency exits immediately aft of the wing, which could result in 
reduced structural integrity of the fuselage pressure vessel.

DATES: Comments must be received by August 31, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 98-NM-169-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,

[[Page 40851]]

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 98-NM-169-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. 98-NM-169-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 series airplanes. The 
DGAC advises that it has received reports indicating that corrosion was 
detected on the fuselage skin panels, between frames 55 and 58, from 
stringers 13 to 31, left and right, in the area surrounding the 
emergency exits. Investigation revealed that on several airplanes, the 
corrosion was extensive enough to require partial or complete 
replacement of the fuselage skin panels. The possible cause of the 
corrosion of the fuselage skin panels may be attributed to the methods 
used in the manufacturing of the skin panels. The manufacturing methods 
have since changed, which has resulted in improved corrosion 
resistance. Such corrosion of the fuselage skin panels that surround 
the emergency exits immediately aft of the wing, if not detected and 
corrected, could result in reduced structural integrity of the fuselage 
pressure vessel.

Explanation of Relevant Service Information

    The manufacturer has issued Airbus Industrie Service Bulletin A300-
53-301, dated September 28, 1995, and Revision 1, dated February 20, 
1997, which describes procedures for repetitive visual inspections to 
detect corrosion on the fuselage skin panels that surround the 
emergency exits immediately aft of the wing, between frames 55 to 58, 
and from stringers 13 to 31, left and right; and follow-on corrective 
actions, if necessary. The follow-on corrective actions include 
removing the corrosion; measuring the remaining thickness of the 
fuselage skin; applying (optional) flap peen; and applying corrosion 
protection finish. Additionally, for any affected area that cannot be 
reworked within certain allowable limits, the service bulletins 
describe procedures for repair by installing a doubler, or partially or 
completely replacing the fuselage skin panel, which would eliminate the 
need for the repetitive inspections of the affected areas. 
Accomplishment of the actions specified in the service bulletins is 
intended to adequately address the identified unsafe condition. The 
DGAC classified these service bulletins as mandatory and issued French 
airworthiness directive 97-357-231(B), dated November 19, 1997, 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 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.

Cost Impact

    The FAA estimates that 24 airplanes of U.S. registry would be 
affected by this proposed AD, that it would take approximately 2 work 
hours 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 
$2,880, or $120 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

    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.

[[Page 40852]]

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.

Sec. 39.13  [Amended]

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

Airbus Industrie: Docket 98-NM-169-AD.

    Applicability: Model A300 series airplanes, as listed in Airbus 
Industrie Service Bulletin A300-53-301, Revision 1, dated February 
20, 1997; 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 (b) 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 corrosion on the fuselage skin panels that 
surround the emergency exits immediately aft of the wing, which 
could result in reduced structural integrity of the fuselage 
pressure vessel, accomplish the following:
    (a) Within 18 months after the effective date of this AD, 
perform a visual inspection to detect corrosion on the fuselage skin 
panels that surround the emergency exits immediately aft of the 
wing, between frames 55 to 58, and from stringers 13 to 31, left and 
right; in accordance with Airbus Industrie Service Bulletin A300-53-
301, dated September 28, 1995, or Revision 1, dated February 20, 
1997.
    (1) If no corrosion is detected, repeat the inspection 
thereafter at intervals not to exceed 18 months on all areas on the 
fuselage skin panels that do not have a doubler installed or areas 
that have not been partially or completely replaced.
    (2) If any corrosion is detected, prior to further flight, 
accomplish rework and perform a residual thickness measurement, in 
accordance with the service bulletin.
    (i) If the measurement does not exceed the allowable limits 
specified by the Accomplishment Instructions of the service 
bulletin, repeat the inspection thereafter at intervals not to 
exceed 18 months.
    (ii) If the measurement does exceed the allowable limits 
specified by the Accomplishment Instructions of the service 
bulletin, prior to further flight, repair using a doubler, or 
replace the affected areas of the skin panel the installation of a 
new skin panel (partially or completely), in accordance with the 
service bulletin. Accomplishment of either action constitutes 
terminating action for the repetitive inspections required by this 
AD for the repaired area or the replaced panel sections only.

    Note 2: Inspections, repairs, and replacements of the fuselage 
skin panels that surround the emergency exits immediately aft of the 
wing that have been accomplished prior to the effective date of this 
AD, in accordance with Airbus Industrie Service Bulletin A300-53-
301, dated September 28, 1995, are considered acceptable for 
compliance with the applicable action specified in this proposed AD.

    (b) 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.

    (c) 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 4: The subject of this AD is addressed in French 
airworthiness directive 97-357-231(B), dated November 19, 1997.

    Issued in Renton, Washington, on July 24, 1998.
D. L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-20437 Filed 7-30-98; 8:45 am]
BILLING CODE 4910-13-U