[Federal Register: May 7, 2004 (Volume 69, Number 89)]
[Proposed Rules]
[Page 25511-25514]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr07my04-15]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NM-13-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B2 and A300 B4; Model
A300 B4-600, B4-600R, C4-605R Variant F, and F4-600R (Collectively
Called A300-600); and Model A310 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to all Airbus Model A300 B2 and A300
B4; Model A300 B4-600, B4-600R, C4-605R Variant F, and F4-600R
(collectively called A300-600); and Model A310 series airplanes. This
proposal would require a detailed inspection of certain pulleys and
control cables in the rear fuselage for corrosion and damage; and
corrective action, if necessary. This action is necessary to detect and
correct frayed or corroded control cables for the elevator and rudder,
which could result in a ruptured control cable, and possible reduced
controllability of the airplane. This action is intended to address the
identified unsafe condition.
DATES: Comments must be received by June 7, 2004.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2003-NM-13-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9 a.m. and 3 p.m., Monday through Friday, except
Federal holidays. Comments may be submitted via fax to (425) 227-1232.
Comments may also be sent via the Internet using the following address:
9-anm-nprmcomment@faa.gov. Comments sent via fax or the Internet must
contain ``Docket No. 2003-NM-13-AD'' in the subject line and need not
be submitted in triplicate. Comments sent via the Internet as attached
electronic files must be formatted in Microsoft Word 97 or 2000 or
ASCII text.
The service information referenced in the proposed rule may be
obtained from Airbus, 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: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2125; fax (425) 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 action may be changed in
light of the comments received.
Submit comments using the following format:
Organize comments issue-by-issue. For example, discuss a
request to change the compliance time and a request to change the
service bulletin reference as two separate issues.
For each issue, state what specific change to the proposed
AD is being requested.
Include justification (e.g., reasons or data) for each
request.
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
[[Page 25512]]
proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this action must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 2003-NM-13-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-114, Attention: Rules
Docket No. 2003-NM-13-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC),
which is the airworthiness authority for France, notified the FAA that
an unsafe condition may exist on all Airbus Model A300 B2 and A300 B4;
Model A300 B4-600, B4-600R, C4-605R Variant F, and F4-600R
(collectively called A300-600); and Model A310 series airplanes. The
DGAC advises that, during a scheduled maintenance visit on an A310
series airplane, an operator found two frayed and corroded elevator
control cables, and one frayed and corroded rudder control cable in the
unpressurized stabilizer compartment at the rear of the fuselage. This
condition, if not corrected, could result in a ruptured control cable,
and possible reduced controllability of the airplane.
The subject area on certain Model A300 B2 and A300 B4; and Model
A300 B4-600, B4-600R, C4-605R Variant F, and F4-600R (collectively
called A300-600) series airplanes is almost identical to that on the
affected Model A310 series airplane. Therefore, those Model A300 B2 and
A300 B4; and Model A300 B4-600, B4-600R, C4-605R Variant F, and F4-600R
(collectively called A300-600) series airplanes may be subject to the
same unsafe condition revealed on the Model A310 series airplanes.
Explanation of Relevant Service Information
Airbus has issued the following service bulletins.
For Model A300 B2 and A300 B4 series airplanes: Airbus
Service Bulletin A300-27A0197, Revision 01, including Appendix 01,
dated February 26, 2003;
For Model A300 B4-600, B4-600R, C4-605R Variant F, and F4-
600R (collectively called A300-600) series airplanes: Airbus Service
Bulletin A300-27A6051, including Appendix 01, dated August 8, 2002; and
For Model A310 series airplanes: Airbus Service Bulletin
A310-27A2098, including Appendix 01, dated August 8, 2002.
These service bulletins describe procedures for a one-time visual
inspection for corrosion and damage (e.g., frayed or broken wires) of
the pulleys and cables of the rudder, elevator, trimmable horizontal
stabilizer, and rudder trim control located at the rear fuselage. These
service bulletins also contain an Inspection Record Sheet in Appendix
01 for reporting inspection findings to the manufacturer.
For airplanes on which no damage is found, the service bulletins
describe procedures for lubricating and testing the cables following
the inspection. For airplanes on which any damage is found that is
within certain limits defined by the applicable aircraft maintenance
manual (AMM), the service bulletins allow further flight. For airplanes
on which any damage is found that is outside the AMM limits, the
service bulletins describe procedures for corrective actions. The
corrective actions include replacing the cables prior to further
flight, and lubricating and testing the cables.
The DGAC classified these service bulletins as mandatory and issued
French airworthiness directive 2002-608(B) R1, dated January 8, 2003,
to ensure the continued airworthiness of these airplanes in France.
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 require accomplishment of
the actions specified in the service bulletin described previously,
except as discussed below.
Differences Among the French Airworthiness Directive, the Service
Bulletins, and the Proposed AD
The French airworthiness directive does not define the type of
inspection, and the service bulletins state that operators should
``visually inspect'' the affected cables. This proposed AD defines the
inspection as a ``detailed inspection.'' A definition of this
inspection is included in Note 1 of this proposed AD.
The service bulletins do not specify a compliance time for sending
the inspection report to the manufacturer, and the French airworthiness
directive specifies compliance within the month following the
inspection. This proposed AD would require reporting the inspection
findings to the manufacturer within 60 days after the proposed
inspection. We find that this information is necessary for the
manufacturer to gather based upon the importance of the safety issue.
We also find that reporting within 60 days ensures an appropriate
interval of time for operators to comply with this proposed requirement
without compromising safety.
Clarification of Inspection Thresholds
The service bulletins and the French airworthiness directive give
inspection thresholds in terms of flight hours accumulated (20,000, 25,
000, and 30,000 total flight hours) on the affected airplanes, well as
the number of years since new (10, 13, and 16 years). We have expressed
these thresholds in paragraph (c) of this proposed AD in a manner that
captures the intent of the service bulletins and French airworthiness
directive, and ensures that all affected airplanes are covered.
Additionally, in lieu of expressing thresholds as a number years
``since new,'' the proposed AD specifies those thresholds as the
earlier of the date of issuance of the original Airworthiness
Certificate, or the original Export Certificate of Airworthiness. This
decision is based on our determination that operators may interpret
``since new'' differently. We find that our proposed terminology is
generally understood within the industry, and records will always exist
that establish these dates with certainty.
Interim Action
We consider this proposed AD interim action. If final action is
later identified, we may consider further rulemaking then.
Cost Impact
The FAA estimates that 174 airplanes of U.S. registry would be
affected by this
[[Page 25513]]
proposed AD, that it would take approximately 1 work hour per airplane
to accomplish the proposed inspection. The average labor rate is $65
per work hour. Based on these figures, the cost impact of the proposed
AD on U.S. operators is estimated to be $11,310, or $65 per airplane.
The cost impact figure discussed above is based on assumptions that
no operator has yet accomplished any of the proposed requirements of
this AD action, and that no operator would accomplish those actions in
the future if this proposed 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 incidental costs, such as the
time required to gain access and close up, planning time, or time
necessitated by other administrative actions.
Regulatory Impact
The regulations proposed herein would 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 proposal would not have federalism implications
under Executive Order 13132.
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 adding the following new
airworthiness directive:
Airbus: Docket 2003-NM-13-AD.
Applicability: All Model A300 B2 and A300 B4; Model A300 B4-600,
B4-600R, C4-605R Variant F, and F4-600R (collectively called A300-
600); and Model A310 series airplanes; certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To detect and correct frayed or corroded control cables for the
elevator and rudder, which could result in a ruptured control cable,
and possible reduced controllability of the airplane, accomplish the
following:
Definitions
(a) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of the following service bulletins, as
applicable:
(1) For Model A300 B2 and A300 B4 series airplanes: Airbus
Service Bulletin A300-27A0197, Revision 01, including Appendix 01,
dated February 26, 2003;
(2) For Model A300 B4-600, B4-600R, C4-605R Variant F, and F4-
600R (collectively called A300-600) series airplanes: Airbus Service
Bulletin A300-27A6051, including Appendix 01, dated August 8, 2002;
and
(3) For Model A310 series airplanes: Airbus Service Bulletin
A310-27A2098, including Appendix 01, dated August 8, 2002.
(b) In this AD, the phrase ``date of airworthiness
certification'' means the date of issuance of the original
Airworthiness Certificate or the original Export Certificate of
Airworthiness, whichever occurs first.
Inspection and Corrective Action
(c) At the applicable time in paragraph (c)(1), (c)(2), (c)(3),
or (c)(4) of this AD, do a detailed inspection for corrosion and
damage (e.g., frayed or broken wires) of the pulleys and cables of
the rudder, elevator, trimmable horizontal stabilizer, and rudder
trim control located at the rear of the fuselage; including any
applicable testing and lubrication following the inspection. If any
corrosion or damage is found that is outside the limits specified in
the service bulletin, prior to further flight, replace the affected
cable with a new cable; including any applicable testing and
lubrication following the replacement. Accomplish all the actions in
accordance with the applicable service bulletin.
(1) For airplanes that have accumulated, as of the effective
date of this AD, less than 20,000 total flight hours and less than
10 years since the date of airworthiness certification: Inspect at
the later of the times specified in paragraphs (c)(1)(i) and
(c)(1)(ii) of this AD.
(i) Prior to the accumulation of 20,000 total flight hours, or
within 10 years since the date of airworthiness certification,
whichever occurs earliest.
(ii) Within 1,800 flight hours after the effective date of this
AD.
(2) For airplanes that have accumulated, as of the effective
date of this AD, either 20,000 or more total flight hours or more
than 10 years since the date of airworthiness certification, but
less than 25,000 total flight hours and 13 years since the date of
airworthiness certification: Inspect at the later of the times
specified in paragraphs (c)(2)(i) and (c)(2)(ii) of this AD.
(i) Prior to the accumulation of 25,000 total flight hours, or
within 13 years since the date of airworthiness certification,
whichever occurs earliest.
(ii) Within 1,800 flight hours after the effective date of this
AD.
(3) For airplanes that have accumulated, as of the effective
date of this AD, either 25,000 or more total flight hours or more
than 13 years since the date of airworthiness certification, but
less than 30,000 total flight hours and 16 years since the date of
airworthiness certification: Inspect at the later of the times
specified in paragraphs (c)(3)(i) and (c)(3)(ii) of this AD.
(i) Prior to the accumulation of 30,000 total flight hours, or
within 16 years since the date of airworthiness certification,
whichever occurs earliest.
(ii) Within 1,200 flight hours after the effective date of this
AD.
(4) For airplanes that have accumulated, as of the effective
date of this AD, either 30,000 or more total flight hours or more
than 16 years since the date of airworthiness certification: Inspect
within 600 flight hours after the effective date of this AD.
Note 1:
For the purposes of this AD, a detailed inspection is defined
as: ``An intensive visual examination of a specific structural area,
system, installation, or assembly to detect damage, failure, or
irregularity. Available lighting is normally supplemented with a
direct source of good lighting at intensity deemed appropriate by
the inspector. Inspection aids such as mirror, magnifying lenses,
etc., may be used. Surface cleaning and elaborate access procedures
may be required.''
Reporting
(d) Submit a report of the findings (both positive and negative)
of the inspection required by paragraph (c) of this AD to Airbus
Industrie, Customer Services Directorate, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; Attn: AI/SE-D32 Technical
Data and Documentation Services, or fax: (+33) 5 61 93 28 06. Send
the report at the applicable time specified in paragraph (c)(1) or
(c)(2) of this AD. The Inspection Record Sheet in Appendix 01 of the
applicable service bulletin may be used. Include the inspection
results, a description of any discrepancy found, the airplane serial
number, the number of landings and flight hours on the airplane, the
service bulletin number, and the date of inspection. Under the
provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et
seq.), the Office of Management and Budget (OMB) has approved the
information collection requirements contained in this AD and has
assigned OMB Control Number 2120-0056.
[[Page 25514]]
(1) If the inspection is done after the effective date of this
AD: Submit the report within 60 days after the inspection.
(2) If the inspection was done prior to the effective date of
this AD: Submit the report within 60 days after the effective date
of this AD.
Alternative Methods of Compliance
(e) 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.
Note 2:
The subject of this AD is addressed in French airworthiness
directive 2002-608(B) R1, dated January 8, 2003.
Issued in Renton, Washington, on April 27, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-10381 Filed 5-6-04; 8:45 am]
BILLING CODE 4910-13-P