[Federal Register Volume 64, Number 213 (Thursday, November 4, 1999)]
[Proposed Rules]
[Pages 60138-60140]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-28847]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-247-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to certain Airbus Model A300, A310, 
and A300-600 series airplanes. This proposal would require either 
replacement of the spring rod assemblies of the rudder servo controls 
with improved spring rod assemblies; or modification of the existing 
spring rod assemblies. For certain airplanes, this proposed AD would 
require a one-time visual inspection to determine whether certain parts 
of the spring rod assemblies of the rudder servo controls are 
installed; and corrective actions, if necessary. This proposal is 
prompted by issuance of mandatory continuing airworthiness information 
by a foreign civil airworthiness authority. The actions specified by 
the proposed AD are intended to prevent corrosion of the spring rod 
assemblies of the rudder servo controls, which could result in the 
jamming of the rudder servo controls and consequent reduced 
controllability of the airplane.

DATES: Comments must be received by December 6, 1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 99-NM-247-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 postcard on which the following statement is made: ``Comments 
to Docket Number 99-NM-247-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. 99-NM-247-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    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 A300, A310, and A300-600 
series airplanes. The DGAC advises that it has received reports of 
jammed spring rods of the rudder servo controls. Investigation revealed 
that the internal mechanism parts of the spring rod assemblies of the 
rudder servo controls were heavily corroded and the drain holes were 
clogged. Such corrosion, if not corrected, could result in the jamming 
of the rudder servo controls

[[Page 60139]]

and consequent reduced controllability of the airplane.

Explanation of Relevant Service Information

    The manufacturer has issued Airbus Service Bulletins A300-27-182, 
Revision 2 (for Model A300 series airplanes); A310-27-2065, Revision 2 
(for Model A310 series airplanes); and A300-27-6023, Revision 2 (for 
Model A300-600 series airplanes); each dated June 30, 1999. These 
service bulletins describe procedures for either replacement of the 
spring rod assemblies of rudder servo controls with improved spring rod 
assemblies, or modification of the existing spring rod assemblies of 
the rudder servo controls. The modification involves enlarging the 
drain holes of the spring rod assembly housing, replacing the 
retainers, and removing the lubrication between the retainer spring and 
rod body. If a modified spring rod assembly is installed, the 
modification also includes re-identification of the modified spring rod 
assembly to the correct part number.
    For certain airplanes, the service bulletins describe procedures 
for a one-time visual inspection to determine whether certain part 
numbers of the spring rod assemblies of the rudder servo controls are 
installed; and corrective actions, if necessary. The corrective actions 
involve re-identifying all spring rod assemblies to the part number 
specified in the service bulletin.
    Accomplishment of the actions specified in the service bulletins is 
intended to adequately address the identified unsafe condition. The 
DGAC classified these service bulletins as mandatory and issued French 
airworthiness directive 1999-240-288(B), dated June 30, 1999, 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 require accomplishment of 
the actions specified in the service bulletin described previously.

Cost Impact

    The FAA estimates that 156 airplanes of U.S. registry would be 
affected by this proposed AD.
    If an operator elects to replace the spring rod assemblies: It 
would take approximately 4 work hours per airplane to accomplish the 
proposed replacement, at an average labor rate of $60 per work hour. 
Required parts would cost approximately $3,720 per airplane. Based on 
these figures, the cost impact of the modification proposed by this AD 
on U.S. operators is estimated to be $3,960 per airplane.
    If an operator elects to modify the spring rod assemblies: It would 
take approximately 7 work hours per airplane to accomplish the proposed 
modification, at an average labor rate of $60 per work hour. Required 
parts would cost approximately $294 per airplane. Based on these 
figures, the cost impact of the proposed AD on U.S. operators is 
estimated to be $714 per airplane.
    If an operator is required to accomplish the one-time inspection: 
It would take approximately 1 work hour per airplane to accomplish that 
proposed inspection, at an average labor rate of $60 per work hour. 
Based on these figures, the cost impact of the proposed AD on U.S. 
operators is estimated to be $60 per airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the proposed 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 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 adding the following new 
airworthiness directive:

Airbus Industrie: Docket 99-NM-247-AD.

    Applicability: Model A300, A310, and A300-600 series airplanes 
except those airplanes on which Airbus Modification 10438 has been 
installed, or Airbus Service Bulletins A300-27-0182, Revision 2, 
A300-27-6023, Revision 2, or A300-27-2065, Revision 2, each dated 
June 30, 1999, 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 corrosion of the spring rod assemblies of the rudder 
servo controls,

[[Page 60140]]

which could result in the jamming of the rudder servo controls and 
consequent reduced controllability of the airplane, accomplish the 
following:
    (a) For airplanes on which the spring rod assemblies of the 
rudder servo controls have not been modified in accordance with 
Airbus Service Bulletin A300-27-182, dated March 16, 1995, or 
Revision 1, dated November 21, 1996 (for Model A300 series 
airplanes); A310-27-2065, dated March 16, 1995, or Revision 1, dated 
March 10, 1997 (for Model A310 series airplanes); or A300-27-6023, 
dated March 16, 1995, or Revision 1, dated March 10, 1997 (for Model 
A300-600 series airplanes); as applicable; as of the effective date 
of this AD: Within 1 year after the effective date of this AD, 
accomplish the actions specified in either paragraph (a)(1) or 
(a)(2) in accordance with Airbus Service Bulletin A300-27-182, 
Revision 2 (for Model A300 series airplanes); or A310-27-2065, 
Revision 2 (for Model A310 series airplanes); or A300-27-6023, 
Revision 2 (for Model A300-600 series airplanes); each dated June 
30, 1999; as applicable.
    (1) Replace the spring rod assemblies with improved spring rod 
assemblies; or
    (2) Modify the existing spring rod assemblies and re-identify 
all modified spring rod assemblies.
    (b) For airplanes on which the spring rod assemblies of the 
rudder servo controls have been modified in accordance with Airbus 
Service Bulletin A300-27-182, dated March 16, 1995, or Revision 1, 
dated November 21, 1996 (for Model A300 series airplanes); or A310-
27-2065, dated March 16, 1995, or Revision 1, dated March 10, 1997 
(for Model A310 series airplanes); or A300-27-6023, dated March 16, 
1995, or Revision 1, dated March 10, 1997 (for Model A300-600 series 
airplanes); as applicable; as of the effective date of this AD: 
Within 1 year after the effective date of this AD, perform a one-
time visual inspection to verify that all spring rod assemblies of 
the rudder servo controls have the same part numbers, in accordance 
with Airbus Service Bulletin A300-27-182, Revision 2 (for Model A300 
series airplanes); or A310-27-2065, Revision 2 (for Model A310 
series airplanes); or A300-27-6023, Revision 2 (for Model A300-600 
series airplanes); each dated June 30, 1999; as applicable.
    (1) If all three spring rod assemblies have either P/N 
A2727086500400 or A2727086500600, no further action is required by 
this AD.
    (2) If any spring rod assembly has a part number other than P/N 
A2727086500400 or A2727086500600, prior to further flight, re-
identify all spring rod assemblies to the part number specified in 
the applicable service bulletin, in accordance with the applicable 
service bulletin.
    (c) As of the effective date of this AD, no person shall install 
on any airplane a spring rod assembly having P/N A2727086500200.

Alternative Methods of Compliance

    (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.

Special Flight Permits

    (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.

    Note 3: The subject of this AD is addressed in French 
airworthiness directive 1999-240-288(B), dated June 30, 1999.

    Issued in Renton, Washington, on October 29, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-28847 Filed 11-3-99; 8:45 am]
BILLING CODE 4910-13-U