[Federal Register Volume 62, Number 208 (Tuesday, October 28, 1997)]
[Rules and Regulations]
[Pages 55726-55728]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-28320]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-NM-155-AD; Amendment 39-10177; AD 97-22-06]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to all Airbus Model A300, A310, and A300-600 series 
airplanes, that requires performing a ram air turbine (RAT) extension 
test; removing and disassembling the RAT uplock mechanism; performing 
an inspection to detect corrosion of the RAT uplock mechanism, and 
replacement with a new assembly, if necessary; and cleaning all the 
parts of the RAT control shaft and its bearing component parts. This 
amendment 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 this 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: Effective December 2, 1997.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of December 2, 1997.

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: Manager, International Office, ANM-
113, 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 all Airbus Model A300, A310, and 
A300-600 series airplanes was published in the Federal Register on 
February 19, 1997 (62 FR 7380). That action proposed to require a RAT 
extension test during ground testing; removal and disassembly of the 
RAT uplock mechanism; a visual inspection to detect corrosion of the 
RAT uplock mechanism, and replacement of the assembly with new parts, 
if necessary; and cleaning of the lever assembly and its associated 
parts.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Revision of Descriptive Language

    One commenter points out that throughout the proposed AD it 
references ram air turbine (RAT) uplock assembly and lever assembly as 
if these assemblies are the same unit. However, Airbus Service Bulletin 
A310-29-2076, dated April 1, 1996 (which is referenced in the proposal 
as an appropriate source of service information) refers to these 
assemblies as separate units. The FAA finds that clarification of this 
point is necessary.
    The FAA finds that ``RAT uplock assembly'' does not appear in the 
proposed AD, but ``RAT lever assembly'' does. The FAA has determined 
that the phrase ``RAT uplock mechanism,'' which includes both the lever 
assembly and uplock unit, provides a more complete description, than 
the phrase, ``RAT lever assembly.'' The FAA has revised the final rule 
to include reference to ``RAT uplock mechanism'' and added a new NOTE 2 
to provide a definition of that phrase.

Clarification of Requirements

    One commenter points out that paragraph (a) of the proposed AD 
references accomplishment of paragraph (a)(1), (a)(2), (a)(3), and 
(a)(4) of the AD; however, paragraph (a)(3) and (a)(4) of the proposed 
AD are missing. The FAA acknowledges that it inadvertently included a 
reference to paragraphs (a)(3) and (a)(4) in paragraph (a) of the 
proposed AD. The FAA has revised paragraph (a) of the final rule to 
delete these references.

Request To Defer Replacement of Corroded Parts

    One commenter requests that paragraph (a)(2)(ii) be revised to 
allow reinstallation of the corroded part and require its replacement 
within 30 days. The commenter points out that operators would have to 
stock every part of the subject assembly at the inspection stations 
(which is not very practical), or its airplanes would have unnecessary 
time out-of-service while waiting for parts. The FAA has reconsidered 
replacing corroded parts prior to further flight. The FAA finds that 
the cleaning and lubrication procedures of the RAT uplock mechanism can 
be accomplished on a temporary basis, in lieu of replacement of 
corroded parts. However, unlike the 12-month compliance time 
recommended in the Airbus service bulletins specified as the 
appropriate service information for this AD, the FAA has determined 
that the corroded parts must be replaced within 30 days following 
accomplishment of the cleaning and lubrication. The FAA finds that this 
compliance time represents the maximum interval of time allowable 
wherein the subject replacement could reasonably be accomplished, 
uncorroded parts could be obtained, and an acceptable level of safety 
could be maintained. Therefore, the FAA has revised paragraph 
(a)(2)(ii) of the final rule accordingly.

Revision of Compliance Time in Paragraph (a) of this AD

    In addition, the compliance time specified in paragraph (a) of this 
AD has been revised to state, ``30 months since date of manufacture,'' 
rather than ``30 months total time-in-service,'' as stated in the 
proposed rule. This change clarifies that the compliance is to be 
determined based on calendar time, without regard to the amount of time 
for which the airplane is operated.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes previously 
described. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

[[Page 55727]]

Cost Impact

    The FAA estimates that 80 Airbus Model A300, A310, and A300-600 
series airplanes of U.S. registry will be affected by this AD, that it 
will take approximately 10 work hours per airplane to accomplish the 
required 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 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 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:

    97-22-06  Airbus Industrie: Amendment 39-10177. Docket 96-NM-
155-AD.

    Applicability: All Model Airbus 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 since the date of 
manufacture, or within 3 months after the effective date of this AD, 
whichever occurs later: Accomplish the requirements of paragraphs 
(a)(1) and (a)(2) 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); or 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 uplock mechanism of the RAT and 
perform a visual inspection of the uplock mechanism to detect 
corrosion, in accordance with the applicable service bulletin.

    Note 2: For the purposes of this AD, the RAT uplock mechanism 
includes both the lever assembly and uplock unit.

    (i) If no corrosion is detected: Prior to further flight, clean 
and lubricate the uplock mechanism 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 uplock 
mechanism, prior to further flight, accomplish either paragraph 
(a)(2)(ii)(A) or (a)(2)(ii)(B) of this AD in accordance with the 
applicable service bulletin.
    (A) Replace the uplock mechanism with a new part and perform a 
retraction/extension/retraction of the RAT, in accordance with the 
applicable service bulletin. Or
    (B) Clean and lubricate the uplock mechanism and its associated 
parts. Within 30 days following accomplishment of this cleaning and 
lubrication, replace the uplock mechanism with a new part and 
perform a retraction/extension/retraction of the RAT.
    (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 3: 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.
    (e) The actions shall be done in accordance with Airbus Service 
Bulletin A300-29-0108, dated April 1, 1996; Airbus Service Bulletin 
A310-29-2076, dated April 1, 1996; or Airbus Service Bulletin A300-
29-6037, dated April 1, 1996; as applicable. 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 4: The subject of this AD is addressed in French 
airworthiness directive 95-163-182 (B) R2, dated June 5, 1996.

    (f) This amendment becomes effective on December 2, 1997.


[[Page 55728]]


    Issued in Renton, Washington, on October 20, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 97-28320 Filed 10-27-97; 8:45 am]
BILLING CODE 4910-13-P