[Federal Register Volume 62, Number 58 (Wednesday, March 26, 1997)]
[Proposed Rules]
[Pages 14365-14367]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-7683]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 96-NM-165-AD]
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: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of 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 proposal would require 
installation of the previously optional terminating action in 
accordance with the latest service information.

DATES: Comments must be received by May 5, 1997.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 96-NM-165-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00

[[Page 14366]]

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: Chuck 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 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-156-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-165-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On February 8, 1996, the FAA issued AD 96-04-05, amendment 39-9517 
(61 FR 6503, February 21, 1996), applicable to certain Airbus Model 
A300-B2 and -B4 series airplanes, 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 
AD also provides for optional terminating action for the inspection and 
test. 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 requirements of 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.

Actions Since Issuance of Previous Rule

    Since the issuance of AD 96-04-05, Airbus has issued Service 
Bulletin A300-78-0015, Revision 2, dated May 24, 1996, as revised by 
Change Notice 2.A., dated May 24, 1996. This service bulletin revision 
describes procedures for replacement of the left and right control 
levers of the thrust reverser with new control levers equipped with new 
springs. The new spring has a 100 percent increase in stiffness and 
possesses a redundant locking device. Accomplishment of the replacement 
eliminates the need for the inspection and operational test. The 
revised service bulletin indicates that, for airplanes on which the 
replacement specified in the original issue or Revision 1 of the 
service bulletin has been accomplished, additional work is necessary.
    The Direction Generale de l'Aviation Civile (DGAC), which is the 
airworthiness authority for France, classified Revision 2 of the 
service bulletin as mandatory and issued French airworthiness directive 
95-185-187(B)R1, dated March 27, 1996, in order to assure the continued 
airworthiness of these airplanes in France. The French airworthiness 
directive specifies that Revision 2 of the service bulletin is the 
appropriate source of service information for accomplishment of the 
replacement, and that the original issue and Revision 1 of the service 
bulletin may not be used to accomplish that action.
    Additionally, it should be noted that, in the preamble of AD 96-04-
05, the FAA indicated that the optional terminating action was 
considered to be ``interim action,'' and that further rulemaking action 
to require that terminating action was being considered. The FAA is now 
proposing to mandate the previously optional terminating action in 
accordance with the latest service bulletin revision described 
previously, rather than in accordance with the original issue of the 
service bulletin, as specified in AD 96-04-05.

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 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.
    The proposed AD also would 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. This action would be required to be accomplished in 
accordance with the service bulletin described previously.
    The optional terminating action that was previously provided for by 
AD 96-04-05 would effectively be removed from the airplane when the 
replacement required by this proposed AD is installed. Additionally, 
for those airplanes on which the previously optional terminating action 
has not been accomplished, no additional work would be required to be 
to install the replacement proposed by this AD.

[[Page 14367]]

Cost Impact

    There are approximately 21 Airbus Model A300-B2 and -B4 series 
airplanes of U.S. registry that would be affected by this proposed 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 on U.S. operators 
of the actions currently required is estimated to be $8,715, or $415 
per airplane.
    The new actions that are proposed in this AD action would take 
approximately 5 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Required parts would cost 
approximately $1,945 per airplane. Based on these figures, the cost 
impact on U.S. operators of the proposed requirements of this AD 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 current or 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 removing amendment 39-9517 (61 FR 
6503, February 21, 1996), and by adding a new airworthiness directive 
(AD), to read as follows:

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

    Applicability: Model A300-B2 and -B4 series airplanes, equipped 
with General Electric CF6-50 series engines or Pratt & Whitney JT9D-
59A engines; certificated in any category.

    Note 1: Model A300-600 series airplanes are not subject to the 
requirements of this AD.

    Note 2: 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 3: 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 4: 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 March 20, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 97-7683 Filed 3-25-97; 8:45 am]
BILLING CODE 4910-13-U