[Federal Register Volume 62, Number 198 (Tuesday, October 14, 1997)]
[Proposed Rules]
[Pages 53269-53272]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-27090]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-77-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A310 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of 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 
action would add 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. This proposal 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

[[Page 53270]]

seizure of two teflon line bearings on the lifting shaft. The actions 
specified by the proposed 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: Comments must be received by November 10, 1997.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 97-NM-77-AD, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056. Comments may be inspected at this location 
between 9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal 
holidays.
    The service information referenced in the proposed rule 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.

FOR FURTHER INFORMATION CONTACT: Charles Huber, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2589; 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 notice may be changed in 
light of the comments received.
    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 proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 97-NM-77-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-103, Attention: Rules 
Docket No. 97-NM-77-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On April 5, 1995, the FAA issued AD 95-08-07, amendment 39-9196 (60 
FR 19155, April 17, 1995), applicable to all Airbus Model A310 series 
airplanes, 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. That action was prompted by 
a report that, during routine maintenance, excessive force was required 
to lift the interior control handle of the emergency exit door. The 
requirements of that 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.

Actions Since Issuance of Previous Rule

    Since issuance of AD 95-08-07, the Direction Generale de l'Aviation 
Civile (DGAC), which is the airworthiness authority for France, advises 
that, during the inspection required by that AD, the seizure of one 
bearing was found on an affected airplane. The DGAC also advises that, 
following accomplishment of the inspection required by that AD, 
increased door handle forces that were outside the limits of the 
required hand forces were required to lift the interior control handle 
of the emergency exit doors. The cause of the excessive force was 
attributed to the seizure of two teflon line bearings on the lifting 
shaft. 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.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletin A310-52-2060, dated July 22, 
1996, which describes procedures for performing repetitive functional 
tests to measure the force necessary to move the interior control 
handle of the emergency exit doors; and adjusting an exit door or 
replacing the bearings of the door lifting mechanism, if necessary. The 
DGAC classified this service bulletin as mandatory and issued French 
airworthiness directive 96-239-205(B), dated October 23, 1996, in order 
to assure the continued airworthiness of these airplanes in France.

FAA's Conclusions

    This airplane model is manufactured in France and is 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 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 proposed AD also would 
require repetitive functional tests to measure the force necessary to 
move the interior control handle of the emergency exit doors; and 
adjusting an exit door or replacing the bearings of the door lifting 
mechanism, if necessary. The actions would be required to be 
accomplished in accordance with the service bulletin described 
previously; except that any discrepancy of the mechanism inside the 
emergency exit door would be required to be repaired in accordance with 
a method approved by the FAA.

Differences Between the Proposal and the Relevant French AD

    This proposed rule would differ from the parallel French 
airworthiness directive 96-239-205(B), in that it would exclude from 
the applicability those airplanes that have been modified in accordance 
with Supplemental Type Certificate (STC) ST0001NY. This STC, which was 
issued by the FAA, converted airplanes from a passenger to a cargo-
carrying configuration. Thus, the emergency exit doors of these 
airplanes are no longer available for use. Therefore, the FAA has 
determined that Airbus Model A310 series airplanes that have been 
modified in accordance with

[[Page 53271]]

the identified STC are not subject to the addressed unsafe condition.

Interim Action

    This is considered to be interim action until final action is 
identified, at which time the FAA may consider further rulemaking.

Cost Impact

    There are approximately 6 Airbus Model A310 series airplanes of 
U.S. registry that would be affected by this proposed 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 proposed in this AD action would 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 proposed 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 current or proposed 
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 proposed herein would 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 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    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 removing amendment 39-9196 (60 FR 
19155, April 17, 1995), and by adding a new airworthiness directive 
(AD), to read as follows:

Airbus Industrie: Docket 97-NM-77-AD. Supersedes AD 95-08-07, 
Amendment 39-9196.

    Applicability: All 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 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,

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Standardization Branch, ANM-113. Operators shall submit their 
requests through 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.

    (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.

    Issued in Renton, Washington, on October 7, 1997.
James V. Devany,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 97-27090 Filed 10-10-97; 8:45 am]
BILLING CODE 4910-13-P