[Federal Register Volume 60, Number 73 (Monday, April 17, 1995)]
[Rules and Regulations]
[Pages 19155-19157]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-8822]
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Rules and Regulations
Federal Register
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Federal Register / Vol. 60, No. 73 / Monday, April 17, 1995 / Rules
and Regulations
[[Page 19155]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-NM-41-AD; Amendment 39-9196; AD 95-08-07]
Airworthiness Directives; Airbus Model A310 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to all Airbus Model A310 series airplanes. This action
requires measurement of the force required to move the interior control
handle of the emergency exit doors, and various follow-on corrective
actions, if necessary. This amendment is prompted by a report that,
during routine maintenance, excessive force was required to lift the
interior control handle of the emergency exit door. The actions
specified in this AD are intended to prevent impeding passenger
evacuation during an emergency due to difficulty in lifting the
interior control handle that is used to open the emergency exit door.
DATES: Effective May 2, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of May 2, 1995.
Comments for inclusion in the Rules Docket must be received on or
before June 16, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 95-NM-41-AD, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056.
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 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.
FOR FURTHER INFORMATION CONTACT: Stephen Slotte, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)
227-2797; fax (206) 227-1320.
SUPPLEMENTARY INFORMATION: The Direction Generale de l'Aviation Civile
(DGAC), which is the airworthiness authority for France, recently
notified the FAA that an unsafe condition may exist on all Airbus Model
A310 series airplanes. The DGAC advises that one operator found, during
routine maintenance, that an excessive amount of force was required to
lift the interior control handle, which opens the left-hand emergency
exit door. Investigation revealed that the seizure of two Teflon-coated
bearings on the lower shaft of the mechanism inside that door caused
the control handle of that emergency exit door to be difficult to lift.
This condition, if not corrected, could impede passenger evacuation
during an emergency due to difficulty in lifting the interior control
handle that is used to open the emergency exit door.
Airbus has issued All Operators Telex (AOT) 52 08, Revision 1,
dated December 1, 1994, which describes procedures for measurement of
the force required to move the interior control handle of the emergency
exit doors, a one-time functional test of the emergency exit doors to
measure the amount of force required to open the doors. Additionally,
for doors on which the force required to open the door exceeds a
certain limit, this AOT describes procedures for a visual inspection to
detect discrepancies of the mechanism inside the door, and replacement
of bearings, if necessary. The French DGAC classified this AOT as
mandatory and issued French airworthiness directive 94-270-172(B),
dated December 7, 1994, in order to assure the continued airworthiness
of these airplanes in France.
This airplane model is manufactured in France and is type
certificated for operation in the United States under the provisions of
Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the
applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the French DGAC has kept the FAA
informed of the situation described above. The FAA has examined the
findings of the French 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.
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, this AD is being issued to prevent impeding
passenger evacuation during an emergency due to difficulty in lifting
the interior control handle that is used to open the emergency exit
door. This AD requires measurement of the force required to move the
interior control handle of the emergency exit door. Additionally this
AD contains several ``on condition'' requirements, including a one-time
functional test of the emergency exit doors to measure the amount of
force required to open the door, a visual inspection to detect
discrepancies of the mechanism inside each emergency exit door, and
replacement of the bearings on the lower shaft of the mechanism inside
the door. The actions are required to be accomplished in accordance
with the AOT described previously.
This AD also requires that certain discrepancies found be repaired
in accordance with a method approved by the FAA. Additionally, this AD
requires that operators submit a report of the findings of
discrepancies to Airbus Industrie.
This is considered to be interim action until final action is
identified, at which time the FAA may consider further rulemaking.
As a result of recent communications with the Air Transport
Association (ATA) of America, the FAA has learned that, in general,
some operators may misunderstand the legal effect of AD's on airplanes
that are identified in the applicability provision of the AD, but that
have been altered or repaired in the area addressed by the AD. The FAA
[[Page 19156]] points out that all airplanes identified in the
applicability provision of an AD are legally subject to the AD. If an
airplane has been altered or repaired in the affected area in such a
way as to affect compliance with the AD, the owner or operator is
required to obtain FAA approval for an alternative method of compliance
with the AD, in accordance with the paragraph of each AD that provides
for such approvals. A note has been included in this rule to clarify
this long-standing requirement.
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this 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 under the caption ADDRESSES. All
communications received on or before the closing date for comments will
be considered, and this rule may be amended in light of the comments
received. Factual information that supports the commenter's ideas and
suggestions is extremely helpful in evaluating the effectiveness of the
AD action and determining whether additional rulemaking action would be
needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the 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 that
summarizes each FAA-public contact concerned with the substance of this
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 95-NM-41-AD.'' The postcard will be date stamped and
returned to the commenter.
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.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and that it is not a ``significant regulatory
action'' under Executive Order 12866. It has been determined further
that this action involves an emergency regulation under DOT Regulatory
Policies and Procedures (44 FR 11034, February 26, 1979). If it is
determined that this emergency regulation otherwise would be
significant under DOT Regulatory Policies and Procedures, a final
regulatory evaluation will be prepared and placed in the Rules Docket.
A copy of it, if filed, 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. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
95-08-07 Airbus Industrie: Amendment 39-9196. Docket 95-NM-41-AD.
Applicability: All Model A310 series airplanes, 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 use the authority
provided in paragraph (e) to request approval from the FAA. This
approval may address either no action, if the current configuration
eliminates the unsafe condition; or different actions necessary to
address the unsafe condition described in this AD. Such a request
should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any airplane from the applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent impeding evacuation during an emergency due to seized
bearings on the lower shaft of the mechanism inside the emergency
exit door, which would make the door control handle difficult to
lift, accomplish the following:
(a) Within 60 days after the effective date of this AD, measure
the amount of force required to move the interior control handle of
the emergency exit doors to, in accordance with Airbus All Operators
Telex (AOT) 52 08, Revision 1, dated December 1, 1994.
(b) If the force required to move the interior control handle of
the door is equal to or does not exceed 20 daN (45 foot-pounds), no
further action is required by this paragraph for that door.
(c) If the force required to move the interior control handle of
the door exceeds 20 daN (45 foot-pounds), prior to further flight,
perform a full functional test of the emergency exit doors to
measure the amount of force required to open the doors, in
accordance with the AOT.
(1) If the force required to open the door is equal to or does
not exceed 20 daN (45 foot-pounds), no further action is required by
this paragraph for that door.
(2) If the force required to open the door exceeds 20 daN (45
foot-pounds), prior to further flight, perform a visual inspection
to detect discrepancies of the mechanism inside the door, in
accordance with the AOT.
(i) If no discrepancy is found, prior to further flight, replace
seized bearings with new or serviceable bearings, in accordance with
the AOT.
(ii) If any discrepancy is found, prior to further flight,
repair the discrepancy in accordance with a method approved by the
Manager, Standardization Branch, ANM-113, FAA, Transport Airplane
Directorate.
(d) Within 10 days after accomplishing the inspection required
by paragraph (a) of this AD, submit a report of the findings of
discrepancies to the Airbus Industrie, Engineering Services,
Attention: Mr. R. Filaquier, AI/SE E121, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France. Information collection
requirements contained in this regulation have been approved by the
Office of Management and Budget (OMB) under the provisions of the
Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq) and have
been assigned OMB Control Number 2120-0056.
(e) 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.
Operators shall submit their requests through [[Page 19157]] an
appropriate FAA Principal Maintenance Inspector, who may add
comments and then send it to the Manager, Standardization Branch,
ANM-113.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(f) Special flight permits may be issued for non-revenue bearing
flights 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.
(g) The measurements, functional test, inspections, and
replacement shall be done in accordance with Airbus All Operators
Telex 52 08, Revision 1, dated December 1, 1994. 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.
(h) This amendment becomes effective on May 2, 1995.
Issued in Renton, Washington, on April 5, 1995.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-8822 Filed 4-14-95; 8:45 am]
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