AD Amdt-39-11458

[Federal Register Volume 64, Number 238 (Monday, December 13, 1999)]
[Rules and Regulations]
[Pages 69386-69388]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 99-31879]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-303-AD; Amendment 39-11458; AD 99-25-15]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.


[[Page 69387]]


ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain Airbus Model A300, A310, 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. This amendment requires, 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. This amendment is prompted by issuance 
of mandatory continuing airworthiness information by a foreign civil 
airworthiness authority. The actions specified by this 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.

DATES: Effective January 18, 2000.

    The incorporation by reference of certain publications listed in 
the regulations was approved previously by the Director of the Federal 
Register as of August 12, 1998 (63 FR 36832, July 8, 1998).
    The incorporation by reference of certain other publications listed 
in the regulations is approved by the Director of the Federal Register 
as of January 18, 2000.

ADDRESSES: 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 Federal 
Aviation Administration (FAA), Transport Airplane Directorate, Rules 
Docket, 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, Transport Airplane Directorate, 1601 
Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-
2110; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 98-14-13, 
amendment 39-10646 (63 FR 36832, July 8, 1998), which is applicable to 
certain Airbus Model A300, A310, A300-600 series airplanes, was 
published in the Federal Register on October 5, 1999 (64 FR 53953). The 
action proposed 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 action also proposed to 
continue to require eventual modification of the free fall control 
mechanism of the landing gear, which constitutes terminating action for 
the repetitive functional tests. Additionally, the action proposed, for 
certain airplanes, that the modification be accomplished in accordance 
with a corrected version of the manufacturer's service bulletin.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

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 will be affected by this AD.
    It will 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.
    It will 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 will 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 will 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 will 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 will 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.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the 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 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:

[[Page 69388]]

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), 
amendment 39-11458, to read as follows:

99-25-15  Airbus Industrie: Amendment 39-11458. 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:
    <bullet> 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;
    <bullet> Model A310 series airplanes on which Airbus 
Modification 02781 has been accomplished and on which Airbus 
Modification 03433 has not been accomplished; and
    <bullet> 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 (e) 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.

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 
Secs. 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.

Incorporation by Reference

    (g) The actions shall be done in accordance with Airbus 
Industrie All Operator Telex 32-14, dated February 3, 1997; Airbus 
Industrie All Operator Telex 32-14, Revision 01, dated March 13, 
1997; Airbus Industrie Service Bulletin A300-32-0425, Revision 02, 
dated June 23, 1998; Airbus Industrie Service Bulletin A300-32-6072, 
Revision 02, dated June 23, 1998; or Airbus Industrie Service 
Bulletin A310-32-2111, Revision 02, dated June 23, 1998; as 
applicable.
    (1) The incorporation by reference of Airbus Industrie Service 
Bulletin A300-32-0425, Revision 02, dated June 23, 1998; Airbus 
Industrie Service Bulletin A300-32-6072, Revision 02, dated June 23, 
1998; and Airbus Industrie Service Bulletin A310-32-2111, Revision 
02, dated June 23, 1998, are approved by the Director of the Federal 
Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) The incorporation of reference of Airbus Industrie All 
Operator Telex 32-14, dated February 3, 1997; Airbus Industrie All 
Operator Telex 32-14, Revision 01, dated March 13, 1997, were 
approved previously by the Director of the Federal Register as of 
August 12, 1998 (63 FR 36832, July 8, 1998).
    (3) 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 5: The subject of this AD is addressed in French 
airworthiness directive 97-113-221(B) R2, dated August 12, 1998.

    (h) This amendment becomes effective on January 18, 2000.

    Issued in Renton, Washington, on December 3, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-31879 Filed 12-10-99; 8:45 am]
BILLING CODE 4910-13-U