[Federal Register Volume 63, Number 82 (Wednesday, April 29, 1998)]
[Rules and Regulations]
[Pages 23374-23376]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-11075]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-NM-143-AD; Amendment 39-10499; AD 98-09-18]
RIN 2120-AA64
Airworthiness Directives; Airbus Industrie Model A320 and A321
Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Airbus Industrie Model A320 and A321 series
airplanes, that requires replacement of two elevator aileron computers
(ELAC) with ELAC's that contain new software. This amendment is
prompted by a report indicating difficulty maintaining the intended
flight path during landing in turbulent conditions. The actions
specified by this AD are intended to prevent situations that could lead
to reduced controllability of the airplane due to adverse airplane-
pilot coupling characteristics.
DATES: Effective June 3, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of June 3, 1998.
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: Norman B. Martenson, Manager,
International Branch, ANM-116, 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 certain Airbus Industrie Model
A320 and A321 series airplanes was published in the Federal Register on
January 7, 1997 (62 FR 949). That action proposed to require
replacement of two elevator aileron computers (ELAC) with ELAC's that
contain new software.
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.
Two commenters support the proposed rule.
One commenter, Airbus, does not object to the proposed AD, but
offers the following comments suggesting changes for clarity and
accuracy. The commenter requests that the statement of unsafe
condition, ``To prevent reduced controllability of the airplane due to
problems associated with the ELAC, accomplish the following: * * *,''
be replaced with, ``In order to adapt lateral control law to real flap
position in case of failure/jamming of flaps, and in order to harmonize
the lateral behavior between `full' and `3' configurations, in
turbulence, of the ELAC, accomplish the following: * * *.'' The
commenter states that its proposed wording of the unsafe condition is
supported by the fact that the improvement of the ELAC is the result of
an in-service event that arose from three conditions surrounding that
event:
--Very strong turbulence during landing preparation;
--Flaps locked between ``full'' and ``3'' configurations resulting from
flaps extension under strong turbulent conditions, the monitoring of
the interconnecting strut between inner and outer flap having detected
an abnormal surfaces displacement; and
--An electronic centralized aircraft monitor (ECAM) procedure
requesting to select slat/flap lever to ``conf 3'' when flaps are
locked between configurations ``3'' and ``full'' (lever in position
``full'').
Additionally, the commenter notes that no system failure initiated the
reported event. In conjunction with its
[[Page 23375]]
request, the commenter also questions the accuracy of a number of
statements made in the notice of proposed rulemaking (NPRM), such as
whether the uncommanded roll angle experienced was actually as great as
30 degrees.
The FAA concurs partially. The FAA agrees that the statement of
unsafe condition should be revised. However, the FAA does not agree
with the commenter's suggested wording of the unsafe condition. The FAA
notes that the preamble of the proposed rule indicates that the unsafe
condition is due to uncommanded movements of the ailerons. The FAA
finds that a more accurate statement of the unsafe condition would
include the fact that it is actually associated with pilot response
coupled with the handling characteristics of the airplane. In light of
this, the FAA has revised the statement of unsafe condition throughout
this final rule to state that the actions specified by this AD are
intended to prevent situations that could lead to reduced
controllability of the airplane due to adverse airplane-pilot coupling
characteristics.
The commenter also notes that the proposed AD refers to part number
C12370AAA01 in error. The FAA has revised the final rule to specify the
correct part number: C12370AA01.
The commenter indicates that the referenced service bulletin has
been revised from the original issue to Revision 1. The FAA
acknowledges that Airbus has issued Service Bulletin A320-27-1082,
Revision 1, dated September 6, 1995, since the issuance of the proposed
rule. This service bulletin revision contains essentially the same
information as that specified in the original issue of the service
bulletin; however, the ELAC Configuration Chart (Figure 1) and the
effectivity listing of the service bulletin has been revised in
Revision 1 to reduce the number of affected airplanes. In light of
this, the applicability of the final rule has been revised to reference
Revision 1 of the service bulletin. In addition, since compliance with
either the original issue or Revision 1 of the service bulletin is
acceptable, the final rule has been revised to cite Revision 1 of the
service bulletin as an additional source of service information.
One commenter states that the cost impact information included in
the proposed AD specifies that 108 Model A320 and A321 series airplanes
would be affected. The commenter notes that no Model A321 series
airplanes are currently on the U.S. Register. The FAA acknowledges this
remark; however, the cost of compliance is the same regardless of
whether all 108 airplanes are A320's or some A321's are included. The
AD applies to Model A321 series airplanes, as well as Model A320 series
airplanes, to ensure compliance in the event one or more affected Model
A321 series airplanes is imported after the effective date of this AD.
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.
Cost Impact
The FAA estimates that 108 Model A320 and A321 series airplanes of
U.S. registry will be affected by this AD, that it will take
approximately 3 work hours per airplane to accomplish the required
actions, and that the average labor rate is $60 per work hour. Required
parts will be provided by the manufacturer at no cost to operators.
Based on these figures, the cost impact of the AD on U.S. operators is
estimated to be $19,440, or $180 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:
98-09-18 Airbus: Amendment 39-10499. Docket 95-NM-143-AD.
Applicability: Model A320 and A321 series airplanes; as listed
in Airbus Service Bulletin A320-27-1082, Revision 1, dated September
6, 1995; 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 (b) 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 prevent situations that could lead to reduced controllability
of the airplane due to adverse airplane-pilot coupling
characteristics, accomplish the following:
(a) Within 1 year after the effective date of this AD, replace
the ELAC's having part numbers (P/N) 3945122307 and/or P/N
C12370AA01 and located in aft electronics rack 80VU, with modified
ELAC's having P/N 3945122502, in accordance with Airbus Service
Bulletin A320-27-1082, dated April 25, 1995, or Revision 1, dated
September 6, 1995.
Note 2: Airbus Service Bulletin A320-27-1082 references Sextant
Service Bulletins 394512-27-014, dated August 11, 1995 (for
airplanes on which Airbus Modification 24136P3436 has not been
installed); and C12370A-27-001, dated May 2, 1995 (for airplanes on
which Airbus Modification
[[Page 23376]]
24136P3436 has been installed); as additional sources of procedural
service information for modification of the ELAC's.
(b) 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, International Branch, ANM-116, 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, International
Branch, ANM-116.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the International Branch, ANM-116.
(c) Special flight permits may be issued in accordance with
Secs. 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.
(d) The actions shall be done in accordance with Airbus Service
Bulletin A320-27-1082, dated April 25, 1995, or Airbus Service
Bulletin A320-27-1082, Revision 1, dated September 6, 1995. Revision
1 contains the specified effective pages:
------------------------------------------------------------------------
Revision
Page no. level shown Date shown on page
on page
------------------------------------------------------------------------
1-2, 4-10, 12-14............. 1............ September 6, 1995.
3, 11, 15.................... Original..... April 25, 1995.
------------------------------------------------------------------------
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 (C/N) 95-203-072(B), dated October 11, 1995,
as corrected by Erratum dated November 8, 1995.
(e) This amendment becomes effective on June 3, 1998.
Issued in Renton, Washington, on April 21, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-11075 Filed 4-28-98; 8:45 am]
BILLING CODE 4910-13-U