[Federal Register Volume 64, Number 33 (Friday, February 19, 1999)]
[Rules and Regulations]
[Pages 8225-8227]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-3732]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
week.
========================================================================
Federal Register / Vol. 64, No. 33 / Friday, February 19, 1999 /
Rules and Regulations
[[Page 8225]]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-316-AD; Amendment 39-11041; AD 99-04-16]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330 and A340 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Airbus Model A330 and A340 series airplanes. This
action requires a one-time operational test to detect discrepancies of
the delay valves and check valves of the main landing gear (MLG); and
corrective actions, if necessary. This amendment also requires
replacement of the retraction bracket assemblies of the MLG with new or
reworked retraction bracket assemblies. 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 prevent failure of the retraction bracket assemblies of the
MLG, which could result in an undampened extension of the MLG, damage
to the sidestay and attachment structure, and possible collapse of the
MLG.
DATES: Effective March 8, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of March 8, 1999.
Comments for inclusion in the Rules Docket must be received on or
before March 22, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 97-NM-316-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 A330 and
A340 series airplanes. The DGAC advises that, during the finishing
process of the retraction brackets of the MLG, small particles of hot
material may have been embedded into the surface of the retraction
brackets, which may affect the fatigue life of a retraction bracket
assembly. Subsequently, fretting was discovered on the surface of the
bushing holes of the retraction brackets of the MLG, which also may
affect the fatigue life of the retraction bracket assemblies. Failure
of a retraction bracket assembly, if not corrected, could result in an
undampened extension of the MLG, damage to the sidestay and attachment
structure, and possible collapse of the MLG.
Explanation of Relevant Service Information
Airbus has issued Service Bulletins A330-32-3058, Revision 1 (for
Model A330 series airplanes), and A340-32-4082, Revision 01 (for Model
A340 series airplanes), both dated February 25, 1997. These service
bulletins describe procedures for a one-time operational test to detect
discrepancies of the delay valves and check valves of the main landing
gear (MLG); and corrective actions, if necessary. The corrective
actions involve replacing any discrepant delay valve or check valve
with a new delay valve or check valve. A discrepant delay valve or
check valve could indicate that the retraction bracket assembly has
operated at a higher stress level, thereby lowering the fatigue life of
the retraction bracket.
Airbus also has issued Service Bulletins A330-32-3066 (for Model
A330 series airplanes), and A340-32-4092 (for Model A340 series
airplanes), both dated November 18, 1996. These service bulletins
describe procedures for replacing the left and right retraction bracket
assemblies of the MLG with new or reworked retraction bracket
assemblies.
Accomplishment of the actions specified in the service bulletins
described previously is intended to adequately address the identified
unsafe condition. The DGAC classified these service bulletins as
mandatory and issued French airworthiness directives 97-007-042(B)R2
(for Model A330 series airplanes), and 97-008-058(B)R1 (for Model A340
series airplanes), both dated April 9, 1997, in order to assure the
continued airworthiness of these airplanes in France.
Airbus Service Bulletins A330-32-3066 and A340-32-4092 reference
Messier-Dowty Service Bulletins A33/34-32-62, Revision 1, dated October
16, 1996, and A33/34-32-80, Revision 1, dated October 17, 1996 (for
both Model A330 and A340 series airplanes), as additional sources of
service information for replacing the left and right retraction bracket
assemblies of the MLG with new or reworked retraction bracket
assemblies.
FAA's Conclusions
These airplane models are manufactured in France and are type
certificated for operation in the United States under the provisions of
section 21.29 of the 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.
[[Page 8226]]
Explanation of Requirements of the 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 prevent failure of the
retraction bracket assemblies of the MLG, which could result in an
undampened extension of the MLG; damage to the sidestay and attachment
structure, and possible collapse of the MLG. This AD requires
accomplishment of the actions specified in the Airbus service bulletins
described previously.
Cost Impact
None of the airplanes affected by this action are 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 6 work hours to
accomplish the required operational test, at an average labor rate of
$60 per work hour. Based on these figures, the cost impact of the
operational test required by this AD would be $360 per airplane.
It would require approximately 4 to 8 work hours to accomplish the
required replacement, at an average labor rate of $60 per work hour.
Required parts would be provided by the manufacturer at no cost to the
operators. Based on these figures, the cost impact of the replacement
required by this AD would range from $240 to $480 per airplane.
Determination of Rule's Effective Date
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, prior 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 97-NM-316-AD.'' The postcard will be date stamped and
returned to the commenter.
Regulatory Impact
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. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
99-04-16 Airbus Industrie: Amendment 39-11041. Docket 97-NM-316-AD.
Applicability: Model A330 and A340 series airplanes having
retraction bracket part numbers as listed in paragraph 1.A.
(``Effectivity'') of Airbus Service Bulletin A330-32-3058, Revision
1 (for Model A330 series airplanes), or A340-32-4082, Revision 01
(for Model A340 series airplanes), both dated February 25, 1997;
except those airplanes on which Airbus Service Bulletin A330-32-3066
(for Model A330 series airplanes) or A340-32-4092 (for Model A340
series airplanes), both dated November 18, 1996, has been
accomplished; certificated in any category.
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 prevent failure of the retraction bracket assemblies of the
main landing gear (MLG), which could result in an undampened
extension of the MLG, damage to the sidestay and attachment
structure, and possible collapse of the MLG, accomplish the
following:
(a) Prior to the accumulation of 2,400 total landings, or within
200 landings after the effective date of this AD, whichever occurs
later, perform a one-time operational test to detect discrepancies
of the left and right delay valves and check valves of the MLG, in
accordance with Airbus Service Bulletin
[[Page 8227]]
A330-32-3058, Revision 1 (for Model A330 series airplanes), or A340-
32-4082, Revision 01 (for Model A340 series airplanes), both dated
February 25, 1997. If any discrepancy is detected, prior to further
flight, replace any discrepant delay valve or check valve with a new
delay valve or check valve in accordance with the applicable service
bulletin.
(b) Replace the left and right retraction bracket assemblies of
the MLG with new or reworked retraction bracket assemblies in
accordance with Airbus Service Bulletin A330-32-3066 (for Model A330
series airplanes), or A340-32-4092 (for Model A340 series
airplanes), both dated November 18, 1996, at the time specified in
paragraph (b)(1) or (b)(2), of this AD, as applicable.
(1) If no discrepancy is detected during the operational test
required by paragraph (a) of this AD: Accomplish the replacement
prior to the accumulation of 4,300 total landings, or within 200
landings after the effective date of this AD, whichever occurs
later.
(2) If any discrepancy is detected during the operational test
required by paragraph (a) of this AD: Accomplish the replacement
prior to the accumulation of 3,250 total landings, or within 200
landings after the effective date of this AD, whichever occurs
later.
Note 2: Airbus Service Bulletins A330-32-3066 and A340-32-4092
reference Messier-Dowty Service Bulletins A33/34-32-62, Revision 1,
dated October 16, 1996, and A33/34-32-80, Revision 1, dated October
17, 1996 (for both Model A330 and A340 series airplanes), as
additional sources of service information for replacing the left and
right retraction bracket assemblies of the MLG with new or reworked
retraction bracket assemblies.
(c) As of the effective date of this AD, no person shall install
on any airplane a retraction bracket assembly having part number (P/
N) 201428224, 201428225, 201428226, 201428227, 201428251, 201428252,
201428253, 201428254, 201478207, 201478208, 201478210, 201478211,
201478217, 201478218, 201478220, or 201478221.
(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.
(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 actions shall be done in accordance with Airbus Service
Bulletin A330-32-3066, dated November 18, 1996; Airbus Service
Bulletin A340-32-4092, dated November 18, 1996; Airbus Service
Bulletin A330-32-3058, Revision 1, dated February 25, 1997; or
Airbus Service Bulletin A340-32-4082, Revision 01, dated February
25, 1997, which contains the following list of effective pages:
------------------------------------------------------------------------
Revision level
Page number shown on page shown on page Date shown on page
------------------------------------------------------------------------
1-5............................. 01................ Feb. 25, 1997.
6-10............................ Original.......... Nov. 18, 1996.
------------------------------------------------------------------------
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 directives 97-007-042(B)R2 and 97-008-058(B)R1, both
dated April 9, 1997.
(g) This amendment becomes effective on March 8, 1999.
Issued in Renton, Washington, on February 9, 1999.
John J. Hickey,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-3732 Filed 2-18-99; 8:45 am]
BILLING CODE 4910-13-U
