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

[Federal Register Volume 63, Number 130 (Wednesday, July 8, 1998)]
[Rules and Regulations]
[Pages 36832-36834]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-17912]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-132-AD; Amendment 39-10646; AD 98-14-13]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Airbus Model A300, A310, and A300-600 series 
airplanes. This amendment 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. This amendment 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 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 August 12, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of August 12, 1998.

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, FAA, 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) to include an airworthiness 
directive (AD) that is applicable to certain Airbus Model A300, A310, 
and A300-600 series airplanes was published in the Federal Register on 
May 14, 1998 (63 FR 26742). That action proposed 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. That 
action also proposed to require eventual modification of the free fall 
control mechanism of the landing gear, which constitutes terminating 
action for the repetitive functional tests.

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 required operational test, at an average labor rate of $60 per work 
hour. Based on these figures, the cost impact of the 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 required functional test, at an average labor rate of $60 per work 
hour. Based on these figures, the cost impact of the 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 required modification on the Model A300 and A300-600 series 
airplanes, at an average labor rate of $60 per work hour. Required 
parts will cost

[[Page 36833]]

approximately $2,630 per airplane. Based on these figures, the cost 
impact of the required modification 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 required modification on the 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 required modification 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:

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:

98-14-13  Airbus Industrie: Amendment 39-10646. Docket 98-NM-132-AD.

    Applicability: Model A300, A310, and A300-600 series airplanes; 
on which Airbus Industrie Modification 02781 has been accomplished, 
and on which Airbus Industrie Modification 03433 or 04443 has not 
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 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:
    (a) Within 600 flight hours after the effective date of this AD, 
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 the effective date of this AD, 
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) 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) Within 66 months after the effective date of this AD, modify 
the free fall control mechanism of the landing gear in accordance 
with Airbus Industrie Service Bulletin A300-32-0425, Revision 01 
(for Model A300 series airplanes); A310-32-2111, Revision 01 (for 
Model A310 series airplanes); or A300-32-6072, Revision 01 (for 
Model A300-600 series airplanes); all dated October 10, 1997; as 
applicable. Accomplishment of the modification constitutes 
terminating action for the repetitive functional tests required by 
paragraph (b) of this AD.
    (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 2: 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 the following 
Airbus Industrie service information, as applicable:
    <bullet> All Operator Telex (AOT) 32-14, dated February 3, 1997;
    <bullet> All Operator Telex (AOT) 32-14, Revision 01, dated 
March 13, 1997;
    <bullet> Service Bulletin A300-32-0425, Revision 01, dated 
October 10, 1997;
    <bullet> Service Bulletin A310-32-2111, Revision 01, dated 
October 10, 1997; or
    <bullet> Service Bulletin A300-32-6072, Revision 01, dated 
October 10, 1997.
    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 3: The subject of this AD is addressed in French 
airworthiness directive 97-113-221(B)R1, dated December 3, 1997.

    (g) This amendment becomes effective on August 12, 1998.


[[Page 36834]]


    Issued in Renton, Washington, on June 29, 1998.
Vi L. Lipski,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-17912 Filed 7-7-98; 8:45 am]
BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T05:00:39.986931+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

03032e06a487a6d9adb752b3d29fdc6a18979f52bc22b83e6051b38ab7fb9e72

Text SHA-256

af4c59b1dcc3976d09b3108fac9a6b72d46bd0bab79bd41a88d045f8bb64f71f