[Federal Register: September 14, 2004 (Volume 69, Number 177)]
[Rules and Regulations]
[Page 55326-55329]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr14se04-5]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NM-228-AD; Amendment 39-13793; AD 2004-18-14]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330 and Model A340-200
and -300 Series Airplanes
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 A330 and A340-200 and -300
series airplanes, that currently requires revising the Limitations
Section of the airplane flight manual (AFM) to ensure that the
flightcrew is advised of the proper procedures in the event of
uncommanded movement of a spoiler during flight. This amendment adds
inspections of the function of the pressure relief valves of each
spoiler servo control (SSC), and corrective action if necessary. This
new AD also mandates eventual modification of the SSCs, which
terminates the AFM revision in the existing AD. The actions specified
by this AD are intended to prevent uncommanded movement of a spoiler
during flight, which could result in reduced controllability of the
airplane and consequent significant increased fuel consumption during
flight, which could necessitate an in-flight turn-back or diversion to
an unscheduled airport destination. This action is intended to address
the identified unsafe condition.
DATES: Effective October 19, 2004.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of October 19, 2004.
ADDRESSES: The service information referenced in this AD may be
obtained from Airbus, 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 National Archives
and Records Administration (NARA). For information on the availability
of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2797; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 2002-16-12,
amendment 39-12851 (67 FR 53478, August 16, 2002), which is applicable
to certain Airbus Model A330 and A340 series airplanes, was published
in the Federal Register on April 1, 2004 (69 FR 17091). The action
proposed to continue to require revising the Limitations Section of the
airplane flight manual (AFM) to ensure the flightcrew is advised of the
proper procedures in the event of uncommanded movement of a spoiler
during flight. The proposed AD also would require inspections and
checks of the function of the pressure relief valves of each spoiler
servo control (SSC), and corrective action if necessary. The proposed
AD would also mandate eventual modification of the SSCs, which would
terminate the AFM revision in the existing AD.
Comments
Interested persons have been afforded an opportunity to participate
in the
[[Page 55327]]
making of this amendment. Due consideration has been given to the
comments received.
One commenter supports the proposed AD. One commenter indicates
that it does not own or operate any affected airplanes.
Request To Change Applicability
One commenter reiterates the applicability listed in the French
airworthiness directives referenced in the proposed AD, and issued by
the Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC), which
is the airworthiness authority for France, and suggests that the
applicability specified in the proposed AD be changed to match the
French airworthiness directives.
We do not agree. The applicability specified in the proposed AD was
carried over from AD 2002-16-12, and has not changed. For
clarification, the model designation listed on the type certificate
data sheet, specifying Airbus Model A330 series airplanes, covers the
airplane models identified as ``Airbus Model A330-201, -202, -203, -
223, -243, -301, -321, -322, -323, -341, -342, and -343 airplanes.''
Airbus Model A340-200 and -300 series airplanes covers the airplane
models identified as ``Airbus Model A340-211, -212, -213, and A340-311,
-312, and -313 airplanes.'' In addition, the applicability in the
proposed AD already specifies the part numbers for the SSCs, as does
the effectivity in the French airworthiness directives. No change is
made to the AD in this regard.
Request To Clarify Paragraphs (c) and (d) of the Proposed AD
One commenter states that the repetitive inspection intervals for
SSCs with any malfunction, as specified in paragraph (c) of the
proposed AD, and the repetitive inspection intervals for SSCs with no
malfunction, as specified in paragraph (d) of the proposed AD, are
redundant.
Although the commenter does not make a specific request, we infer
that the commenter is asking for clarification of the repetitive
inspection intervals specified in paragraphs (c) and (d) of the
proposed AD. We agree that some clarification is necessary; therefore,
we have removed the repetitive inspection/check intervals for
functioning SSCs from paragraph (c), and included clarification that
the requirements in paragraph (c) are only for affected SSCs on which a
malfunction is found. In addition, we have included clarification that
the repetitive inspections/checks required by paragraph (d) are only
for affected SSCs on which no malfunction is found.
Requests To Change Compliance Times
One commenter states that there is a difference between the
proposed AD and the referenced French airworthiness directives
regarding the starting date for the initial detailed inspection/
functional check. The commenter also notes that there is a difference
between the proposed AD and the referenced French airworthiness
directives which provide a calendar date for accomplishment of the
terminating action for all SSCs.
Although the commenter does not make a specific request, we infer
that the commenter is asking that the compliance time for the initial
detailed inspection/functional check and the terminating action, as
specified in paragraphs (b) and (e) of the proposed AD, respectively,
be changed to match the compliance times in the French airworthiness
directives.
We do not agree. The French airworthiness directives give a
compliance time for the initial detailed inspection/functional check
based on the original issue date of those airworthiness directives. Due
to some procedural differences in the way we express compliance times,
the compliance time in this AD is presented in a manner that differs
from that in the French airworthiness directives. However, the
compliance time captures the intent of the French airworthiness
directives, and ensures that operators of all affected airplanes are
given sufficient time to accomplish the inspection, while still
ensuring operational safety.
In addition, the compliance time in the French airworthiness
directives for the terminating action specifies a calendar time, but we
do not express compliance times in terms of calendar dates unless an
engineering analysis establishes a direct relationship between the date
and the compliance time. Additionally, a risk assessment done by the
manufacturer and the DGAC, in agreement with the FAA, validates the
compliance times required by this AD.
In light of these factors, we have determined that 700 flight hours
for the initial detailed inspection/functional check, and 13 months for
the terminating action, is appropriate. No change is made to the AD in
this regard.
Another commenter asks that the compliance time for the terminating
action be extended. The commenter states that the actions required by
the proposed AD are best suited for a base maintenance environment. The
commenter adds that the current compliance time of 13 months for
accomplishment of the modification of the SSCs does not coincide with
any scheduled maintenance interval. The commenter asks that the
compliance time be extended to 18 months to correspond with the C-check
interval.
We do not agree that the compliance time for the terminating action
should be extended. As specified in our response above, a risk
assessment done by the manufacturer and the DGAC, in agreement with the
FAA, validates the compliance times required by this AD. No change is
made to the AD in this regard.
Conclusion
We have carefully reviewed the available data, including the
comments that have been submitted, and determined that air safety and
the public interest require adopting the AD with the change described
previously. We have determined that this change will neither increase
the economic burden on any operator nor increase the scope of the AD.
Cost Impact
There are about 14 airplanes of U.S. registry that will be affected
by this AD.
The AFM revision that is currently required by AD 2002-16-12 takes
about 1 work hour per airplane to accomplish, at an average labor rate
of $65 per work hour. Based on these figures, the cost impact of the
currently required AFM revision is estimated to be $65 per airplane.
The new inspections/checks that are required by this AD action will
take about 1 work hour per airplane to accomplish, at an average labor
rate of $65 per work hour. Based on these figures, the cost impact of
the inspections/checks required by this AD on U.S. operators is
estimated to be $910, or $65 per airplane, per inspection/check cycle.
The new modification that is required by this AD action will take
about 15 work hours per airplane to accomplish, at an average labor
rate of $65 per work hour. Required parts will be provided to operators
free of charge. Based on these figures, the cost impact of the
modification required by this AD on U.S. operators is estimated to be
$13,650, or $975 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 that no operator would accomplish those actions in the
future if this AD were not adopted. The cost impact figures discussed
in AD rulemaking actions represent only the time necessary to perform
the specific actions actually required by the AD. These figures
typically do not include
[[Page 55328]]
incidental costs, such as the time required to gain access and close
up, planning time, or time necessitated by other administrative
actions.
Currently, there are no Model A340 series airplanes on the U.S.
Register. However, if an affected airplane is imported and placed on
the U.S. Register in the future, the new inspections/checks in this AD
action would take about 1 work hour, at an average labor rate of $65
per work hour. Based on these figures, we estimate the cost of the
inspections/checks to be $65 per airplane, per inspection/check cycle.
The new modification in this AD action would take about 15 work hours
per airplane to accomplish, at an average labor rate of $65 per work
hour. Required parts would be provided to operators free of charge.
Based on these figures, we estimate the cost of this modification to be
$975 per airplane.
Regulatory Impact
The regulations adopted herein will not have a substantial direct
effect 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, it
is determined that this final rule does not have federalism
implications under Executive Order 13132.
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
0
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
0
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]
0
2. Section 39.13 is amended by removing amendment 39-12851 (67 FR
53478, August 16, 2002), and by adding a new airworthiness directive
(AD), amendment 39-13793, to read as follows:
2004-18-14 Airbus: Amendment 39-13793. Docket 2002-NM-228-AD.
Supersedes AD 2002-16-12, Amendment 39-12851.
Applicability: Model A330 and A340-200 and -300 series
airplanes, certificated in any category; equipped with any spoiler
servo control having part number (P/N) 1386A0000-01, 1386B0000-01,
1387A0000-01, or 1387B0000-01.
Compliance: Required as indicated, unless accomplished
previously.
To ensure that the flightcrew is advised of the proper
procedures in the event of uncommanded movement of a spoiler during
flight, which could result in reduced controllability of the
airplane and consequent significant increased fuel consumption
during flight, and could result in an in-flight turn-back or
diversion to an unscheduled airport destination, accomplish the
following:
Restatement of Requirements of AD 2002-16-12
Revision to Airplane Flight Manual (AFM)
(a) Within 10 days after September 20, 2002 (the effective date
of AD 2002-16-12, amendment 39-12851), revise the Limitations
Section of the AFM by including the procedures listed in Figure 1 of
this AD. This revision may be done by inserting a copy of the
following Figure 1 into the AFM:
Figure 1
``PROCEDURE:
If ``F/CTL SPLR FAULT'' is triggered
--F/CTL S/D
page....................................... CHECK
If the affected spoiler is not
indicated extended amber:
The spoiler is faulty in the retracted
position. In such a case, the specific OEB
procedure does not apply.
--LDG DIST PROC............................ APPLY
Multiply the landing distance by 1.1 for 3
or 4 spoilers lost per wing..
Multiply the landing distance by 1.2 for 5
or 6 spoilers lost per wing..
If the affected spoiler is indicated
extended amber, apply the following procedure:
IN CRUISE
CAUTION
Disregard FMGC fuel predictions, as they do
not take the increase in fuel consumption
into account.
--FUEL CONSUMPTION INCREASE................ APPLY
Apply 18.5% increase in the fuel
consumption..
--IN-FLIGHT TURN BACK/DIVERSION............ CONSIDER
In-flight turn back or diversion may have
to be considered due to this fuel penalty..
--MAX ACHIEVABLE ALTITUDE DECREASE......... CONSIDER
With the maximum spoiler deflection, the
maximum altitude in ISA conditions may
decrease by 4,500 feet..
FOR LANDING
--FOR LDG.................................. USE FLAP 3
Use CONF 3 for landing to avoid possible
buffeting, which, however, may be high
depending on the failed spoiler..
--VAPP..................................... NORM
--LDG DIST................................. x 1.1''
Note 1: When the procedure in paragraph (a) of this AD has been
incorporated into the general revisions of the AFM, the general
revisions may be incorporated into the AFM, provided the procedures
in this AD and the general revisions are identical. This AD may then
be removed from the AFM.
New Requirements of This AD
Initial Detailed Inspection/Functional Check
(b) Within 700 flight hours after the effective date of this AD:
Do a detailed
[[Page 55329]]
inspection/functional check of the blocking function of the pressure
relief valves (PRVs) of affected spoiler servo controls (SSCs) by
doing all the actions in accordance with paragraphs 3.A.,
3.B.(1)(a), 3.D., and 3.E. of the Accomplishment Instructions of
Airbus Service Bulletin A330-27-3090 (for A330 series airplanes) or
A340-27-4096 (for A340-200 and -300 series airplanes), both Revision
02, both dated August 1, 2002, as applicable.
Note 2: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
Note 3: Liebherr Service Bulletin 1386A-27-03, Revision 1, dated
February 4, 2002, is referenced in Airbus Service Bulletins A330-27-
3090 and A340-27-4096, both Revision 02, as an additional source of
service information for accomplishment of the inspections.
Corrective Action
(c) For airplanes having an affected SSC on which any
malfunction is found during the inspection/functional check required
by paragraph (a) of this AD: Before further flight, do the
terminating action required by paragraph (e) of this AD for that
SSC.
(d) For airplanes having affected SSCs on which no malfunction
is found during the inspection/functional check required by
paragraph (a) of this AD: Repeat the inspection/functional check one
time within 1,600 flight hours after accomplishment of the initial
inspection required by paragraph (a) of this AD. If no malfunction
is found, repeat the inspection/functional check thereafter at
intervals not to exceed 2,400 flight hours, until accomplishment of
the terminating action required by paragraph (e) of this AD.
Terminating Action
(e) Except as required by paragraph (c) of this AD: Within 13
months after the effective date of this AD, modify all affected SSCs
by doing all the actions in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330-27-3094 (for A330
series airplanes) or A340-27-4100 (for A340-200 and -300 series
airplanes), both Revision 01, both dated August 1, 2002; as
applicable. Modification of all affected SSCs terminates the
requirements of paragraphs (a), (b), (c), and (d) of this AD. After
the modification has been done, the previously required AFM revision
may be removed.
Note 4: Liebherr Service Bulletin 1386A-27-05, dated February
25, 2002, is referenced in Airbus Service Bulletins A330-27-3094 and
A340-27-4100 as an additional source of service information for
accomplishment of the modification.
Previously Accomplished Actions
(f) Accomplishment of the inspections in accordance with Airbus
Service Bulletins A330-27-3090 and A340-27-4096, both dated
September 28, 2001; or A340-27-4096, Revision 01, dated December 12,
2001; as applicable; is considered acceptable for compliance with
the inspections required by this AD.
(g) Airbus Service Bulletins A330-27-3090 and A340-27-4096, both
dated August 1, 2002, specify to submit inspection results to the
manufacturer, however; this AD does not include that requirement.
Parts Installation
(h) As of the effective date of this AD, no person may install
on any airplane a spoiler servo control having P/N 1386A0000-01,
1386B0000-01, 1387A0000-01, or 1387B0000-01, unless it has been
modified per paragraph (e) of this AD.
Alternative Methods of Compliance
(i) In accordance with 14 CFR 39.19, the Manager, International
Branch, ANM-116, FAA, Transport Airplane Directorate, is authorized
to approve alternative methods of compliance for this AD.
Incorporation by Reference
(j) The actions shall be done in accordance with the applicable
service bulletins listed in Table 1 of this AD, unless the AD
specifies otherwise.
Table 1.--Materials Incorporated by Reference
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Revision
Airbus service bulletin level Date
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A330-27-3090....................... 02 Aug. 1, 2002.
A330-27-3094....................... 01 Aug. 1, 2002.
A340-27-4096....................... 02 Aug. 1, 2002.
A340-27-4100....................... 01 Aug. 1, 2002.
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The Director of the Federal Register approved the incorporation by
reference of these documents in accordance with 5 U.S.C. 552(a) and
1 CFR part 51. You can get copies of the documents from Airbus, 1
Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. You can
review copies at the Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW., room PL-401, Nassif
Building, Washington, DC; or at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
Note 5: The subject of this AD is addressed in French
airworthiness directives 2002-552(B) and 2002-553(B), both dated
November 13, 2002.
Effective Date
(k) This amendment becomes effective on October 19, 2004.
Issued in Renton, Washington, on August 31, 2004.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-20407 Filed 9-13-04; 8:45 am]
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