[Federal Register Volume 62, Number 122 (Wednesday, June 25, 1997)]
[Rules and Regulations]
[Pages 34159-34161]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-16106]



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 Rules and Regulations
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  Federal Register / Vol. 62, No. 122 / Wednesday, June 25, 1997 / 
Rules and Regulations  

[[Page 34159]]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-NM-165-AD; Amendment 39-10050; AD 97-13-04]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300-B2 and -B4 Series 
Airplanes, Excluding Model A300-600 Series Airplanes, Equipped With 
General Electric CF6-50 Series Engines or Pratt & Whitney JT9D-59A 
Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain Airbus Model A300-B2 and -B4 series 
airplanes, that currently requires an inspection to detect 
discrepancies of a certain thrust reverser control lever spring; an 
operational test to verify the integrity of the flight inhibition 
circuit of the thrust reverser system; and either the correction of 
discrepancies or deactivation of the associated thrust reverser. That 
AD also provides for an optional terminating action. That AD was 
prompted by a report that, due to broken and deformed thrust reverser 
control lever springs, an uncommanded movement of the thrust reverser 
lever to the unlock position and a ``reverser unlock'' amber warning 
occurred on one airplane. The actions specified by that AD are intended 
to detect such broken or deformed control lever springs before they 
lead to uncommanded deployment of a thrust reverser and consequent 
reduced controllability of the airplane. This amendment requires 
installation of the previously optional terminating action in 
accordance with the latest service information.

DATES: Effective July 30, 1997.
    The incorporation by reference of Airbus All Operators Telex (AOT) 
78-03, Revision 1, dated July 20, 1994, as listed in the regulations, 
was approved previously by the Director of the Federal Register as of 
March 22, 1996 (61 FR 6503, February 21, 1996).
    The incorporation by reference of Airbus Service Bulletin A300-78-
0015, Revision 2, dated May 24, 1996, as revised by Change Notice 2.A., 
dated May 24, 1996, as listed in the regulations, is approved by the 
Director of the Federal Register as of July 30, 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: Charles Huber, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2589; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 96-04-05, 
amendment 39-9517 (61 FR 6503, February 21, 1996), which is applicable 
to certain Airbus Model A300-B2 and -B4 series airplanes, was published 
in the Federal Register on March 26, 1997 (62 FR 14365). That action 
proposed to supersede AD 96-04-05 to continue to require an inspection 
to detect discrepancies of a certain thrust reverser control lever 
spring; an operational test to verify the integrity of the flight 
inhibition circuit of the thrust reverser system; and either the 
correction of discrepancies or deactivation of the associated thrust 
reverser. That action also proposed to require replacement of the left 
and right control levers of the thrust reverser with new control levers 
equipped with new springs; this replacement would constitute 
terminating action for the inspection and operational test 
requirements.

Explanation of Changes Made to the Proposal

    The FAA has revised the applicability of the proposed AD to 
reference exactly which Model A300-B2 and -B4 series airplane are 
subject to the requirements of the proposed AD. The finds that, as the 
applicability of the proposed AD is currently worded, operators could 
misintrepet it. As a result of this change, the FAA finds that Note 2 
of the proposed AD is no longer necessary. The FAA has revised the 
final rule accordingly.

Consideration of Comments Received

    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 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.

Cost Impact

    There are approximately 21 Airbus Model A300-B2 and -B4 series 
airplanes of U.S. registry that will be affected by this AD.
    The actions that are currently required by AD 96-04-05 take 
approximately 6 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Required parts cost approximately $55 
per airplane. Based on these figures, the cost impact of the previously 
required actions on U.S. operators is estimated to be $8,715, or $415 
per airplane.
    The new actions that are required by this new AD will take 
approximately 5 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Required parts will cost approximately 
$1,945 per airplane. Based on these figures, the cost impact of the new 
requirements of this AD on U.S. operators is estimated to be $47,145, 
or $2,245 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

[[Page 34160]]

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 removing amendment 39-9517 (61 FR 
6503, February 21, 1996), and by adding a new airworthiness directive 
(AD), amendment 39-10050, to read as follows:

97-13-04  Airbus Industrie: Amendment 39-10050. Docket 96-NM-165-AD. 
Supersedes AD 96-04-05, Amendment 39-9517.

    Applicability: Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, 
B4-103, and B4-203 series airplanes, equipped with General Electric 
CF6-50 series engines or Pratt & Whitney JT9D-59A engine; 
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 (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 broken or deformed thrust reverser control lever 
springs before they lead to uncommanded deployment of a thrust 
reverser and consequent reduced controllability of the airplane, 
accomplish the following:

Restatement of Requirements of AD 96-04-05, Amendment 39-9517

    (a) Within 500 flight hours after March 22, 1996 (the effective 
date AD 96-04-05, amendment 39-9517), perform a mechanical integrity 
inspection to detect discrepancies of the thrust reverser control 
lever spring having part number (P/N) A2791294520000, and an 
operational test to verify the integrity of the flight inhibition 
circuit of the thrust reverser system, in accordance with Airbus All 
Operators Telex (AOT) 78-03, Revision 1, dated July 20, 1994.
    (1) If no discrepancies are detected, no further action is 
required by paragraph (a) of this AD.
    (2) If the control lever spring is found broken or out of 
tolerance, prior to further flight, replace it with a new control 
lever spring or deactivate the associated thrust reverser in 
accordance with the AOT.
    (3) If the flight inhibition circuit of the thrust reverser 
system fails the operational test, prior to further flight, 
determine the origin of the malfunction, in accordance with the AOT.
    (i) If the origin of the malfunction is identified, prior to 
further flight, repair the flight inhibition circuit in accordance 
with the AOT.
    (ii) If the origin of the malfunction is not identified, prior 
to further flight, replace the relay having P/N 125GB or 124GB, and 
repeat the operational test, in accordance with the AOT. If the 
malfunction is still present, prior to further flight, inspect and 
repair the wiring in accordance with the AOT. If the malfunction is 
still present following the inspection and repair, prior to further 
flight, deactivate the associated thrust reverser in accordance with 
the AOT.

New Requirements of this AD

    (b) Within 60 days after the effective date of this AD, replace 
the left and right control levers of the thrust reverser with new 
control levers equipped with new springs, in accordance with Airbus 
Service Bulletin A300-78-0015, Revision 2, dated May 24, 1996, as 
revised by Change Notice 2.A., dated May 24, 1996. After 
replacement, no further action is required by this AD.

    Note 2: Accomplishment of the replacement in accordance with 
either the original issue or Revision 1 of Airbus Service Bulletin 
A300-78-0015 is not considered acceptable for compliance with the 
applicable action specified in this AD.

    (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 All 
Operators Telex (AOT) 78-03, Revision 1, dated July 20, 1994; and 
Airbus Service Bulletin A300-78-0015, Revision 2, dated May 24, 
1996, as revised by Change Notice 2.A., dated May 24, 1996, which 
contains the following list of effective pages:

------------------------------------------------------------------------
                                    Revision level                      
            Page No.                 shown on page    Date shown on page
------------------------------------------------------------------------
Change Notice 2.A...............  ..................  May 24, 1996.     
1, 3-16, 19.....................  2.................  May 24, 1996.     
2...............................  1.................  November 22, 1995.
17, 18..........................  Original..........  May 17, 1995.     
------------------------------------------------------------------------

    The incorporation by reference of Airbus AOT 78-03, Revision 1, 
dated July 20, 1994, was approved previously by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51 as of March 22, 1996 (61 FR 6503, February 21, 1996). The 
incorporation by reference of Airbus Service Bulletin A300-78-0015, 
Revision 2, dated May 24, 1996, as revised by Change Notice 2.A., 
dated May 24, 1996, is 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.
    (f) This amendment becomes effective on July 30, 1997.


[[Page 34161]]


    Issued in Renton, Washington, on June 13, 1997.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 97-16106 Filed 6-24-97; 8:45 am]
BILLING CODE 4910-13-U