[Federal Register Volume 64, Number 192 (Tuesday, October 5, 1999)]
[Proposed Rules]
[Pages 53953-53956]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-25769]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-303-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD), applicable to certain Airbus Model A300, 
A310, and A300-600 series airplanes, that currently requires a one-time 
operational test and repetitive functional tests of the free fall 
control mechanism of the landing gear to ensure proper release of the 
main landing gear (MLG), and corrective action, if necessary. It also 
requires eventual modification of the free fall control mechanism of 
the landing gear, which constitutes terminating action for the 
repetitive functional tests. That amendment was prompted by issuance of 
mandatory continuing airworthiness information by a foreign civil 
airworthiness authority. This proposed AD would require, for certain 
airplanes, that the modification of the free fall control mechanism of 
the landing gear be accomplished in accordance with a corrected version 
of the manufacturer's service bulletin. The actions specified by this 
proposal are intended to prevent malfunction of the free fall control 
mechanism of the landing gear, which could result in the inability to 
extend the MLG in the event of failure of the hydraulic extension 
system.

DATES: Comments must be received by November 4, 1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 98-NM-303-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

[[Page 53954]]

postcard on which the following statement is made: ``Comments to Docket 
Number 98-NM-303-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-303-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On June 29, 1998, the FAA issued AD 98-14-13, amendment 39-10646 
(63 FR 36832, July 8, 1998), applicable to certain Airbus Model A300, 
A310, and A300-600 series airplanes, to require a one-time operational 
test and repetitive functional tests of the free fall control mechanism 
of the landing gear to ensure proper release of the main landing gear 
(MLG), and corrective action, if necessary. It also requires eventual 
modification of the free fall control mechanism of the landing gear, 
which constitutes terminating action for the repetitive functional 
tests. That amendment was prompted by issuance of mandatory continuing 
airworthiness information by a foreign civil airworthiness authority. 
The requirements of that AD are intended to prevent malfunction of the 
free fall control mechanism of the landing gear, which could result in 
the inability to extend the MLG in the event of failure of the 
hydraulic extension system.

Actions Since Issuance of Previous Rule

    Since issuance of AD 98-14-13, the manufacturer and the Direction 
Generale de l'Aviation Civile (DGAC), which is the airworthiness 
authority for France, have advised the FAA that an error exists in 
Airbus Service Bulletin A310-32-2111, Revision 01, dated October 10, 
1997. That service bulletin describes procedures for modification of 
the free fall control mechanism of the landing gear on Airbus Model 
A310 series airplanes, and was referenced as the appropriate source of 
service information for the modification of Airbus Model A310 series 
airplanes required by that AD. Certain part numbers shown in that 
service bulletin are incorrect for one of the two telescopic rod 
assemblies of the free fall control mechanism of the MLG. This error 
was corrected in Revision 02, dated June 23, 1998, of Airbus Service 
Bulletin A310-32-2111.
    The FAA now has determined that further rulemaking action is 
necessary to require the modification of Airbus Model A310 series 
airplanes, described previously, to be accomplished in accordance with 
Revision 02 of Airbus Service Bulletin A310-32-2111, and, if the 
modification was installed in accordance with an earlier service 
bulletin revision, removal of the discrepant parts and installation of 
the correct part number parts.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletins A300-32-0425 (for Model A300 
series airplanes), A300-32-6072 (for Model A300-600 series airplanes), 
and A310-32-2111 (for Model A310 series airplanes); all Revision 02; 
all dated June 23, 1998. These service bulletins describe procedures 
for modification of the free fall control mechanism of the landing 
gear. The modification includes removing telescopic rods and cranks or 
crank assemblies from the MLG part of the free fall control mechanism 
of the landing gear, replacing the telescopic rods with new parts, and 
replacing the cranks or crank assemblies with improved parts. 
Accomplishment of the modification eliminates the need for the 
repetitive inspections described previously.
    The procedures for the modification in Revision 02 of the service 
bulletins for Model A300 and A300-600 series airplanes are identical to 
those described in Revision 01 of the service bulletins (which were 
referenced in AD 98-14-13). As discussed previously, the procedures for 
the modification in Revision 02 of the service bulletin for Model A310 
series airplanes differ from those described in Revision 01 of the 
service bulletin (which was referenced in AD 98-14-13) in that certain 
part numbers for one of the two telescopic rod assemblies have been 
corrected in Revision 02.
    Accomplishment of the actions specified in the service bulletins 
described previously is intended to adequately address the identified 
unsafe condition. The DGAC classified the service bulletins as 
mandatory and issued French airworthiness directive 97-113-221(B) R2, 
dated August 12, 1998, 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 
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 supersede AD 98-14-13 to 
continue to require a one-time operational test and repetitive 
functional tests of the free fall control mechanism of the landing gear 
to ensure proper release of the main landing gear (MLG), and corrective 
action, if necessary. The proposed AD would continue to require 
eventual modification of the free fall control mechanism of the landing 
gear, which constitutes terminating action for the repetitive 
functional tests. The actions would be required to be accomplished in 
accordance with the service bulletins described previously. This action 
would require, for certain airplanes, that the modification of the free 
fall control mechanism of the landing gear be accomplished in 
accordance with a later corrected version of the manufacturer's service 
bulletin.

Explanation of Compliance Time for Model A310 Series Airplanes

    Operators should note that, while the appropriate source of service 
information that would be required for this AD for Model A310 series 
airplanes has changed, the compliance time remains the same. The FAA 
has determined that the compliance time, as proposed, represents an 
appropriate interval in which the modification can be accomplished in 
accordance with Revision 02 of Airbus Service Bulletin A310-32-2111 in 
a timely manner and still maintain an adequate level of safety.

Cost Impact

    The FAA estimates that 24 Model A300 series airplanes, 41 Model 
A310 series airplanes, and 61 Model A300-600 series airplanes of U.S. 
registry would be affected by this proposed AD.
    It would take approximately 3 work hours per airplane to accomplish 
the currently required operational test, at an average labor rate of 
$60 per work hour. Based on these figures, the cost impact of the 
currently required operational test on U.S. operators is estimated to 
be $22,680, or $180 per airplane.

[[Page 53955]]

    It would take approximately 2 work hours per airplane to accomplish 
the currently required functional test, at an average labor rate of $60 
per work hour. Based on these figures, the cost impact of the currently 
required functional test on U.S. operators is estimated to be $15,120, 
or $120 per airplane, per test cycle.
    It would take approximately 26 work hours per airplane to 
accomplish the currently required modification on Model A300 and A300-
600 series airplanes, at an average labor rate of $60 per work hour. 
Required parts would cost approximately $2,630 per airplane. Based on 
these figures, the cost impact of the currently required actions on 
U.S. operators of Model A300 or A300-600 series airplanes is estimated 
to be $356,150, or $4,190 per airplane.
    It would take approximately 28 work hours per airplane to 
accomplish the modification on Model A310 series airplanes, at an 
average labor rate of $60 per work hour. Required parts would cost 
approximately $3,710 per airplane. Based on these figures, the cost 
impact of the currently required actions on U.S. operators of Model 
A310 series airplanes is estimated to be $220,990, or $5,390 per 
airplane.

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.

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 removing amendment 39-10646 (63 FR 
36832, July 8, 1998), and by adding a new airworthiness directive (AD), 
to read as follows:

Airbus Industrie: Docket 98-NM-303-AD. Supersedes AD 98-14-13, 
Amendment 39-10646.

    Applicability: Model A300, A300-600, and A310 series airplanes, 
certificated in any category, as identified below:
     Model A300 and A300-600 series airplanes on which 
Airbus Modification 02781 has been accomplished and on which neither 
Airbus Modification 03433 nor 04443 has been accomplished;
     Model A310 series airplanes on which Airbus 
Modification 02781 has been accomplished and on which Airbus 
Modification 03433 has not been accomplished; and
     Model A310 series airplanes on which Airbus Service 
Bulletin A310-32-2111, dated March 10, 1997, or Revision 01, dated 
October 10, 1997; has been accomplished.

    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 malfunction of the free fall control mechanism of the 
landing gear, which could result in the inability to extend the main 
landing gear (MLG) in the event of failure of the hydraulic 
extension system, accomplish the following:

Restatement of Actions Required by AD 98-14-13, Amendment 39-10646

    (a) Within 600 flight hours after August 12, 1998 (the effective 
date of AD 98-14-13, amendment 39-10646), perform a one-time 
operational test of the free fall control mechanism of the landing 
gear to ensure proper release of the MLG for extension by free fall, 
in accordance with Airbus Industrie All Operator Telex (AOT) 32-14, 
dated February 3, 1997, or Revision 01, dated March 13, 1997. If any 
discrepancy is detected in the functioning of the free fall control 
mechanism of the landing gear, prior to further flight, readjust the 
mechanism and repeat the operational test in accordance with the 
AOT. If any discrepancy is detected in the second operational test, 
prior to further flight, rerig the free fall control mechanism in 
accordance with the AOT, and accomplish the actions required by 
paragraph (b) of this AD.
    (b) Within 10 months after August 12, 1998, perform a functional 
test of the free fall control mechanism of the landing gear to 
ensure proper release of the MLG for extension by free fall, in 
accordance with Airbus Industrie AOT 32-14, dated February 3, 1997, 
or Revision 01, dated March 13, 1997. Thereafter, repeat the 
functional test of the free fall control mechanism of the landing 
gear at intervals not to exceed 12 months, until the modification 
required by paragraph (c) or (d) of this AD has been accomplished. 
During any test performed in accordance with paragraph (b) of this 
AD, if the free fall control mechanism of the landing gear fails to 
fully extend the MLG, prior to further flight, readjust or rerig the 
mechanism in accordance with the AOT.
    (c) For Model A300 and A300-600 series airplanes: Within 66 
months after August 12, 1998, modify the free fall control mechanism 
of the landing gear in accordance with Airbus Industrie Service 
Bulletin A300-32-0425, Revision 02 (for Model A300 series 
airplanes); or A300-32-6072, Revision 02 (for Model A300-600 series 
airplanes); each dated June 23, 1998; as applicable. Accomplishment 
of the modification constitutes terminating action for the 
repetitive functional tests required by paragraph (b) of this AD.

    Note 2: Modifications accomplished in accordance with Airbus 
Industrie Service Bulletin A300-32-0425, Revision 01 (for Model A300 
series airplanes); or A300-32-6072, Revision 01 (for Model A300-600 
series airplanes); each dated October 10, 1997; are acceptable for 
compliance with the requirements of paragraph (c) of this AD.

New Actions Required by This AD

    (d) For Model A310 series airplanes: Within 66 months after 
August 12, 1998, modify the free fall control mechanism of the 
landing gear in accordance with Airbus Industrie Service Bulletin 
A310-32-2111, Revision 02, dated June 23, 1998. Accomplishment of 
the modification constitutes terminating action for the repetitive 
functional tests required by paragraph (b) of this AD.

    Note 3: For Airbus Model A310 series airplanes, only a 
modification accomplished in accordance with Airbus Industrie 
Service Bulletin A310-32-2111, Revision 02, dated June 23, 1998, is 
acceptable for compliance with the requirements of paragraph (d) of 
this AD.

[[Page 53956]]

Alternative Methods of Compliance

    (e) 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 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

Special Flight Permits

    (f) 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 5: The subject of this AD is addressed in French 
airworthiness directive 97-113-221(B) R2, dated August 12, 1998.

    Issued in Renton, Washington, on September 28, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-25769 Filed 10-4-99; 8:45 am]
BILLING CODE 4910-13-P