[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