[Federal Register Volume 60, Number 113 (Tuesday, June 13, 1995)]
[Rules and Regulations]
[Pages 31073-31075]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-13890]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 95-NM-45-AD; Amendment 39-9259; AD 95-12-09]


Airworthiness Directives; Airbus Model A300 B4-1C, B4-2C, B4-203 
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), 
applicable to certain Airbus Model A300 series airplanes. This action 
requires repetitive inspections to detect cracking in the hinge 
fittings of the nose landing gear (NLG) aft doors, and replacement of 
cracked fittings. This amendment is prompted by several reports of loss 
of an NLG aft door during landing, due to failure of the door's hinge 
fittings. The actions specified in this AD are intended to prevent the 
loss of an NLG aft door due to the failure of the hinge fittings; such 
loss of a door can result in damage to the surrounding aircraft 
structure or injury to persons on the ground.

DATES: Effective on June 28, 1995.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 28, 1995.
    Comments for inclusion in the Rules Docket must be received on or 
before August 14, 1995.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 95-NM-45-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: Stephen Slotte, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue SW., Renton, Washington 98055-4056; telephone (206) 
227-2797; fax (206) 227-1320.

SUPPLEMENTARY INFORMATION: The Direction Generale de l'Aviation Civile 
(DGAC), which is the airworthiness authority for France, recently 
notified the FAA that an unsafe condition may exist on certain Airbus 
Model A300 B4-1C, B4-2C, and B4-203 series airplanes. The DGAC advises 
that there have been four incidents in which an aft (secondary) door of 
the nose landing gear (NLG) on in-service airplanes was lost during 
landing. The doors separated from the airplanes due to rupture of the 
doors' forward hinge fitting. The cause of the fitting failures has 
been attributed to fatigue cracking. Such cracking, if not detected and 
corrected in a timely manner, can lead to separation of the NLG aft 
door from the airplane. Loss of a door can result in damage to the 
surrounding aircraft structure or injury to persons on the ground.
    Airbus Industrie has issued Service Bulletin A300-52-0161, dated 
October 3, 1994, which describes procedures for performing repetitive 
eddy current inspections of the NLG aft door hinge fittings. This 
service bulletin also describes procedures for replacing cracked 
fittings. The DGAC approved this service bulletin as mandatory in order 
to assure the continued airworthiness of these airplanes in France.
    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 [[Page 31074]] Federal Aviation Regulations (14 
CFR 21.19) 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.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design, this AD is 
being issued to prevent the loss of an NLG aft door due to the failure 
of the door's hinge fittings. This AD requires repetitive eddy current 
inspections to detect cracking of the hinge fittings, and replacement 
of any hinge fitting found to be cracked. Inspections continue after 
replacement of a hinge fitting is accomplished. The actions are 
required to be accomplished in accordance with the service bulletin 
described previously.
    As a result of recent communications with the Air Transport 
Association (ATA) of America, the FAA has learned that, in general, 
some operators may misunderstand the legal effect of AD's on airplanes 
that are identified in the applicability provision of the AD, but that 
have been altered or repaired in the area addressed by the AD. The FAA 
points out that all airplanes identified in the applicability provision 
of an AD are legally subject to the AD. If an airplane has been altered 
or repaired in the affected area in such a way as to affect compliance 
with the AD, the owner or operator is required to obtain FAA approval 
for an alternative method of compliance with the AD, in accordance with 
the paragraph of each AD that provides for such approvals. A note has 
been included in this AD to clarify this long-standing requirement.
    There currently are no affected Model A300 B4-C, B4-2C, or B4-203 
series airplanes on the U.S. Register. All airplanes included in the 
applicability of this rule currently are operated by non-U.S. operators 
under foreign registry; therefore, they are not directly affected by 
this AD action. However, the FAA considers that this rule is necessary 
to ensure that the unsafe condition is addressed in the event that any 
of these subject airplanes are imported and placed on the U.S. Register 
in the future.
    Should an affected airplane be imported and placed on the U.S. 
Register in the future, it would require approximately 3 work hours to 
accomplish the required actions, at an average labor charge of $60 per 
work hour. Based on these figures, the total cost impact of this AD 
would be $180 per airplane per inspection cycle.
    Since this AD action does not affect any airplane that is currently 
on the U.S. register, it has no adverse economic impact and imposes no 
additional burden on any person. Therefore, notice and public 
procedures hereon are unnecessary and the amendment may be made 
effective in less than 30 days after publication in the Federal 
Register.

Comments Invited

    Although this action is in the form of a final rule and was not 
preceded by notice and 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 95-NM-45-AD.'' The postcard will be date stamped and 
returned to the commenter.
    The regulations adopted herein will 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 final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it 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. App. 1354(a), 1421 and 1423; 49 U.S.C. 
106(g); and 14 CFR 11.89.


Sec. 39.13  [Amended]

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

95-12-09  Airbus Industrie: Amendment 39-9259. Docket 95-NM-45-AD.

    Applicability: Model A300 B4-1C, B4-2C and B4-203 series 
airplanes; having serial numbers 002 through 019, inclusive; 
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 use the authority 
provided in paragraph (d) to request approval from the FAA. This 
approval may address either no action, if the current configuration 
eliminates the unsafe condition; or different actions necessary to 
address the unsafe condition described in this AD. Such a request 
should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any airplane from the applicability of this AD.

    [[Page 31075]] Compliance: Required as indicated, unless 
accomplished previously.
    To prevent the loss of a nose landing gear (NLG) aft door due to 
the failure of the door's hinge fittings, which can result in damage 
to the surrounding aircraft structure or injury to persons on the 
ground, accomplish the following:
    (a) Prior to the accumulation of 8,000 total flight cycles, or 
within 500 flight cycles after the effective date of this AD, 
whichever occurs later, perform an eddy current inspection to detect 
cracks in the hinge fitting of the NLG left- and right-hand aft 
doors, in accordance with Airbus Service Bulletin A300-52-0161, 
dated October 3, 1994.
    (b) If no crack(s) is found during the inspection required by 
paragraph (a) of this AD, repeat the eddy current inspection 
thereafter at intervals not to exceed 700 flight cycles.
    (c) If any crack is found during the inspection required by 
paragraph (a) of this AD, prior to further flight, replace the hinge 
fittings in accordance with Airbus Service Bulletin A300-52-0161, 
dated October 3, 1994. Within 8,000 flight cycles after this 
replacement, and thereafter at intervals not to exceed 700 flight 
cycles, perform an eddy current inspection to detect cracking of the 
hinge fittings, in accordance with the service bulletin.
    (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, Standardization Branch, ANM-113, 
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, 
Standardization Branch, ANM-113.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Standardization Branch.

    (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.
    (f) The inspection and replacement actions shall be done in 
accordance with Airbus Service Bulletin A300-52-0161, dated October 
3, 1994. 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.
    (g) This amendment becomes effective on June 28, 1995.

    Issued in Renton, Washington, on June 1, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-13890 Filed 6-12-95; 8:45 am]
BILLING CODE 4910-13-U