[Federal Register Volume 63, Number 53 (Thursday, March 19, 1998)]
[Rules and Regulations]
[Pages 13333-13335]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-6760]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-77-AD; Amendment 39-10400; AD 98-06-22]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310 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 all Airbus Model A310 Series Airplanes, that
currently 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 adds
repetitive functional tests to measure the force necessary to move the
interior control handle of the emergency exit doors; and requires
adjusting an emergency exit door or replacing the bearing of the door
lifting mechanism, if necessary. This amendment is prompted by reports
of seizure of a bearing and increased door handle forces that were
outside the limits of the required hand forces due to seizure of two
teflon line bearings on the lifting shaft. The actions specified by
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 April 23, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of April 23, 1998.
The incorporation by reference of Airbus All Operators Telex 52 08,
Revision 1, dated December 1, 1994, was approved previously by the
Director of the Federal Register as of May 2, 1995 (60 FR 19155, April
17, 1995).
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) by superseding AD 95-08-07,
amendment 39-9196 (60 FR 19155, April 17, 1995), which is applicable to
all Airbus Model A310 series airplanes, was published in the Federal
Register on October 14, 1997 (62 FR 53269). The action proposed to
supersede AD 95-08-07 to continue to require measurement of the force
required to move the interior control handle of the emergency exit
doors, and various follow-on corrective actions, if necessary. The
action also proposed to require repetitive functional tests to measure
the force necessary to move the interior control handle of the
emergency exit doors; and adjusting an emergency exit door or replacing
the bearing of the door lifting mechanism, if necessary.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
Request for Additional Functional Testing
One commenter requests that testing of the force required to open
the door be accomplished at least three times during accomplishment of
the functional test. The commenter states that this would aid in
identifying cases where the door handle force was very close to the
limit.
The FAA does not concur with the commenter's request. The
procedures described in the referenced service information indicate
that the emergency exit door is to be moved at least three times into
the closed position, and lifted each time. Additionally, the service
information specifies that the operation of the door should be assessed
during the lifting process for an aligned movement; since the movement
of the interior control handle is smooth, constant hand force is
required. In light of this, the FAA finds that the requirements of this
AD, as proposed, are adequate to address the identified unsafe
condition.
Request for Pre-Flight Checks
The commenter also requests that a requirement be added to the
proposal to check the handle force on a pre-flight basis to ensure that
the force would not exceed the limit shortly after the inspection is
performed. The
[[Page 13334]]
commenter indicates that the manner in which Teflon bearings fail is
gradual.
The FAA does not concur with the commenter's request. In developing
the proposed inspection interval of three months, the FAA has
determined that this interval is appropriate in light of the safety
implications, the average utilization rate of the affected fleet, and
the practical aspects of an orderly inspection of the fleet during
regular maintenance periods.
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 as proposed.
Cost Impact
There are approximately 6 airplanes of U.S. registry that will be
affected by this AD.
The actions that are currently required by AD 95-08-07 take
approximately 1 work hour per airplane to accomplish, at an average
labor rate of $60 per work hour. Based on these figures, the cost
impact of the currently required actions on U.S. operators is estimated
to be $360, or $60 per airplane.
The new actions that are required by this new AD will take
approximately 1 work hour per airplane to accomplish, at an average
labor rate of $60 per work hour. Based on these figures, the cost
impact of the new requirements of this AD on U.S. operators is
estimated to be $360, or $60 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.
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 39-9196 (60 FR
19155, April 17, 1995), and by adding a new airworthiness directive
(AD), amendment 39- , to read as follows:
98-06-22 Airbus Industrie: Amendment 39-10400. Docket 97-NM-77-AD.
Supersedes AD 95-08-07, Amendment 39-9196.
Applicability: Model A310 series airplanes, except those
airplanes that have been modified in accordance with Supplemental
Type Certificate (STC) ST0001NY; 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 (f) 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 impeding passenger evacuation during an emergency due
to difficulty in lifting the interior control handle that is used to
open the emergency exit door, accomplish the following:
Restatement of Requirements of AD 95-08-07, Amendment 39-9196
(a) Within 60 days after May 2, 1995 (the effective date of AD
95-08-07), measure the amount of force required to move the interior
control handle of the emergency exit doors, 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 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
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 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.
New Requirements of This AD
(e) Within 3 months after the effective date of this AD, perform
a functional test to measure the force necessary to move the
interior control handle of the emergency exit doors, in accordance
with Airbus Service Bulletin A310-52-2060, dated July 22, 1996.
(1) If the emergency exit door opens and the force required to
move the interior control hand is less than or equal to the limits
specified in the service bulletin, repeat the test thereafter at
intervals not to exceed 3 months.
(2) If the emergency exit door does not open or the force
required to move the interior handle is greater than the limits
specified in the service bulletin, prior to further flight, perform
an inspection to detect discrepancies of the mechanisms inside the
door, in accordance with the service bulletin.
(i) If no discrepancy is detected, prior to further flight,
replace the bearings with new
[[Page 13335]]
bearings, in accordance with the service bulletin. Repeat the test
thereafter at intervals not to exceed 3 months.
(ii) If any discrepancy is detected, prior to further flight,
adjust the emergency exit doors in accordance with the service
bulletin. Repeat the test thereafter at intervals not to exceed 3
months.
(f) 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 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the International Branch, ANM-116.
(g) 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.
(h) The actions shall be done in accordance with Airbus All
Operators Telex (AOT) 52 08, Revision 1, dated December 1, 1994; and
Airbus Service Bulletin A310-52-2060, dated July 22, 1996.
(1) The incorporation by reference of Airbus Service Bulletin
A310-52-2060, dated July 22, 1996, is approved by the Director of
the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) The incorporation by reference of Airbus AOT 52 08, Revision
1, dated December 1, 1994, was approved previously by the Director
of the Federal Register as of May 2, 1995 (60 FR 19155, April 17,
1995).
(3) 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 3: The subject of this AD is addressed in French
airworthiness directive 96-239-205(B), dated October 23, 1996.
(i) This amendment becomes effective on April 23, 1998.
Issued in Renton, Washington, on March 10, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-6760 Filed 3-18-98; 8:45 am]
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