[Federal Register Volume 62, Number 33 (Wednesday, February 19, 1997)]
[Proposed Rules]
[Pages 7380-7382]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-3965]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 96-NM-155-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 all Airbus Model A300, A310, and 
A300-600 series airplanes. This proposal would require performing a ram 
air turbine (RAT) extension test; removing and disassembling the RAT 
lever assembly; performing an inspection to detect corrosion of the RAT 
lever assembly, and replacement with a new assembly, if necessary; and 
cleaning all the parts of the RAT control shaft and its bearing 
component parts. This proposal is prompted by reports indicating that 
the RAT did not extend during ground testing, due to corrosion in the 
uplock pin/shaft and the needle bearing of the RAT. The actions 
specified by the proposed AD are intended to detect and correct such 
corrosion of the RAT, which could result in failure of the RAT to 
deploy and subsequent loss of emergency hydraulic power to the flight 
controls in the event that power is lost in both engines.

DATES: Comments must be received by March 31, 1997.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 96-NM-155-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: Charles Huber, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 
227-2589; fax (206) 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

[[Page 7381]]

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 96-NM-155-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-103, Attention: Rules 
Docket No. 96-NM-155-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The Direction Gonorale de l'Aviation Civile (DGAC), which is the 
airworthiness authority for France, recently notified the FAA that an 
unsafe condition may exist on all Airbus Model A300, A310, and A300-600 
series airplanes. The DGAC advises that it has received reports 
indicating that the ram air turbine (RAT) did not extend during ground 
tests. Investigation revealed that the non-extension of the RAT was due 
to corrosion of the RAT control shaft and its bearing needles between 
the uplock unit and the lever connected to the control linkage. 
Corrosion of the RAT uplock pin/shaft and needle, if not detected and 
corrected in a timely manner, could result in failure of the RAT to 
deploy and subsequent loss of emergency hydraulic power to the flight 
controls in the event that power is lost in both engines.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletin A300-29-0108 (for Model A300 
series airplanes), Service Bulletin A310-29-2076 (for Model A310 series 
airplanes), and Service Bulletin A300-29-6037 (for Model A300-600 
series airplanes), all dated dated April 1, 1996, which describe 
procedures for the following:
    1. Performing a RAT extension test during ground testing;
    2. Removing and disassembling the RAT lever assembly (uplock 
assembly);
    3. Performing a visual inspection to detect corrosion of the RAT 
lever assembly; and
    4. Cleaning all the parts of the RAT lever assembly and all its 
associated parts.
    The service bulletins also describe procedures for replacing any 
corroded parts with new parts. They also describe procedures for 
cleaning and lubricating corroded parts in lieu of replacement with new 
parts, in situations where new parts are not readily available.
    The DGAC classified these service bulletins as mandatory and issued 
French airworthiness directive, 95-163-182(B)R2, dated June 5, 1996, 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 a RAT extension 
test during ground testing; removal and disassembly of the RAT lever 
assembly; a visual inspection to detect corrosion of the RAT lever 
assembly, and replacement of the assembly with new parts, if necessary; 
and cleaning of the lever assembly and its associated parts. The 
actions would be required to be accomplished in accordance with the 
service bulletins described previously.

Differences Between Proposed AD and Referenced Service Bulletins

    Operators should note that, although the Airbus service bulletins 
describe certain cleaning and lubrication procedures of the RAT lever 
assembly that can be accomplished in lieu of replacement of corroded 
parts, this proposed AD would not permit those actions as an 
alternative to replacement. The FAA finds that, to ensure an adequate 
level of safety for the affected fleet, corroded parts must be replaced 
prior to further flight. The FAA has determined that, in cases where 
known unsafe conditions exist and where actions to detect and correct 
those unsafe conditions can be readily accomplished, those actions must 
be required.

Interim Action

    This is considered to be interim action until final action is 
identified, at which time the FAA may consider further rulemaking.

Cost Impact

    The FAA estimates that 80 Airbus Model A300, A310, and A300-600 
series airplanes of U.S. registry would be affected by this proposed 
AD, that it would take approximately 10 work hours per airplane to 
accomplish the proposed actions, and that the average labor rate is $60 
per work hour. Required parts would be provided by the manufacturer at 
no cost to the operator. Based on these figures, the cost impact of the 
proposed AD on U.S. operators is estimated to be $48,000, or $600 per 
airplane.
    The cost impact figure discussed above is 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

[[Page 7382]]

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 96-NM-155-AD.

Applicability: All Model A300, A310, and A300-600 series airplanes, 
certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
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 (c) 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 detect and correct corrosion of the ram air turbine (RAT) 
uplock pin/shaft and needle that could result in failure of the RAT 
to deploy and subsequent loss of emergency hydraulic power to the 
flight controls in the event that power is lost in both engines, 
accomplish the following:
    (a) Prior to the accumulation of 30 months total time-in-
service, or within 3 months after the effective date of this AD, 
whichever occurs later: Accomplish the requirements of paragraphs 
(a)(1), (a)(2), (a)(3), and (a)(4) of this AD in accordance with 
Airbus Service Bulletin A300-29-0108, dated April 1, 1996 (for Model 
A300 series airplanes); A310-29-2076, dated April 1, 1996 (for Model 
A310 series airplanes); A300-29-6037, dated April 1, 1996 (for Model 
A300-600 series airplanes); as applicable. Thereafter, repeat these 
actions at intervals not to exceed 30 months.
    (1) Perform a RAT extension test on the ground, in accordance 
with the procedures specified in the Maintenance Manual.
    (2) Disassemble and remove the lever assembly of the RAT and 
perform a visual inspection of the lever assembly to detect 
corrosion, in accordance with the applicable service bulletin.
    (i) If no corrosion is detected: Prior to further flight, clean 
and lubricate the lever assembly and its associated parts, reinstall 
the assembly, and perform a retraction/extension/retraction of the 
RAT, in accordance with the applicable service bulletin.
    (ii) If any corrosion is detected in any part of the lever 
assembly: Prior to further flight, replace the lever assembly with a 
new part and perform a retraction/extension/retraction of the RAT, 
in accordance with the applicable service bulletin.
    (b) Initial accomplishment of the actions required by paragraph 
(a) of this AD that have been performed in accordance with Airbus 
All Operator Telex (AOT) 29-16, Revision 01, dated January 10, 1996, 
is considered acceptable for compliance with the initial RAT 
extension test and an initial visual inspection as required by 
paragraph (a) of this AD. However, the first repetitive inspection, 
as required by paragraph (a) of this AD, must be performed within 30 
months after that RAT extension test and visual inspection were 
conducted, and repeated thereafter at intervals not to exceed 30 
months.
    (c) 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, Standardization Branch, ANM-113, 
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, 
Standardization Branch, ANM-113.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Standardization Branch, ANM-113.

    (d) 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.

    Issued in Renton, Washington, on February 11, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 97-3965 Filed 2-18-97; 8:45 am]
BILLING CODE 4910-13-U