[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
Federal Register
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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:
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Revision level
Page No. shown on page Date shown on page
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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.
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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]
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