[Federal Register Volume 63, Number 129 (Tuesday, July 7, 1998)]
[Proposed Rules]
[Pages 36622-36624]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-17958]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-307-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to all Airbus Model A300, A310, and 
A300-600 series airplanes. This proposal would require repetitive 
visual inspections to detect cracked or broken door stop fittings on 
the fuselage frame of the forward passenger doors, and replacement of 
any cracked or broken fitting with a new fitting. 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

[[Page 36623]]

cracked or broken door stop fittings of the forward passenger doors, 
which could result in failure of the door stop fittings, consequent 
reduced structural integrity of the door support structure, and sudden 
loss of cabin pressure in the passenger compartment.

DATES: Comments must be received by August 6, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 97-NM-307-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 97-NM-307-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. 97-NM-307-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 all Airbus Model A300, A310, and A300-600 series 
airplanes. The DGAC advises that, during full scale fatigue testing of 
Airbus Model A330 and A340 series airplanes, cracked and broken door 
stop fittings were discovered on the fuselage frame of the left and 
right forward passenger doors. The broken door stops were found between 
27,000 and 60,000 simulated flight cycles. As a result of these 
findings, another analysis of fatigue loading on Model A300, A310, and 
A300-600 series airplanes was performed. The results of this analysis 
demonstrated that similar fractures also may occur on these airplanes 
because of the design similarities. Such cracked or broken door stop 
fittings, if not detected and corrected, could result in failure of the 
door stop fittings, consequent reduced structural integrity of the door 
support structure, and sudden loss of cabin pressure in the passenger 
compartment.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletins A300-53-0309 (for Model A300 
series airplanes); A310-53-2087 (for Model A310 series airplanes); and 
A300-53-6060 (for Model A300-600 series airplanes); all dated March 19, 
1997; which describe procedures for repetitive visual inspections to 
detect cracked or broken door stop fittings on the fuselage frame of 
the forward passenger doors, and replacement of any cracked or broken 
fitting with a new fitting. 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 97-124-223(B), 
dated June 4, 1997, 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 
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.

Differences Between Proposed Rule and Service Bulletin

    Operators should note that, although the Airbus service bulletins 
reference the Master Minimum Equipment List (MMEL) for appropriate 
compliance times for repair of cracked or broken door stop fittings, 
this proposed AD would not permit further flight if cracks are detected 
in the door stop fittings. The FAA has determined that, because of the 
safety implications and consequences associated with such cracking, any 
subject door stop fitting that is found to be cracked, must be replaced 
prior to further flight.

Cost Impact

    The FAA estimates that 103 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 
$12,360, 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

[[Page 36624]]

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, 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 97-NM-307-AD.

    Applicability: All Model A300, A310, and A300-600 series 
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 (c) 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 cracked or broken door stop fittings of 
the forward passenger doors, which could result in failure of the 
door stop fittings, consequent reduced structural integrity of the 
door support structure, and sudden loss of cabin pressure in the 
passenger compartment, accomplish the following:
    (a) Prior to the accumulation of the total flight cycles 
specified in the ``Threshold'' column of paragraph 1.B.(5) of the 
Planning Information of Airbus Service Bulletin A300-53-0309 (for 
Model A300 series airplanes); A310-53-2087 (for Model A310 series 
airplanes); or A300-53-6060 (for Model A300-600 series airplanes); 
all dated March 19, 1997; as applicable; or within 200 flight cycles 
after the effective date of this AD, whichever occurs later; 
accomplish paragraphs (a)(1) and (a)(2) of this AD.
    (1) Perform a visual inspection of the left and right forward 
passenger door stop fittings to detect cracked or broken door stop 
fittings, in accordance with the applicable service bulletin. And
    (2) Thereafter, repeat the visual inspection at the intervals 
specified in the ``Intervals'' column of paragraph 1.B.(5) of the 
Planning Information of the applicable service bulletin.
    (b) If any cracked or broken door stop fitting is detected 
during any inspection required by paragraph (a)(1) or (a)(2) of this 
AD, prior to further flight, replace the door stop fitting with a 
new fitting in accordance with Airbus Service Bulletin A300-53-0309 
(for Model A300 series airplanes); A310-53-2087 (for Model A310 
series airplanes); or A300-53-6060 (for Model A300-600 series 
airplanes); all dated March 19, 1997; as applicable. Thereafter, 
repeat the visual inspections at the intervals specified in the 
``Intervals'' column of paragraph 1.B.(5) of the Planning 
Information of the applicable service bulletin.
    (c) 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.

    (d) 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 97-124-223(B), dated June 4, 1997.

    Issued in Renton, Washington, on June 30, 1998.
Stewart R. Miller,
Acting Manager,
Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 98-17958 Filed 7-6-98; 8:45 am]
BILLING CODE 4910-13-P