[Federal Register Volume 59, Number 167 (Tuesday, August 30, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-21362]


[[Page Unknown]]

[Federal Register: August 30, 1994]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 94-NM-94-AD]

 

Airworthiness Directives; Airbus Model A320 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 certain Airbus Model A320 series 
airplanes. This proposal would require repetitive inspections to verify 
proper installation of the plain bushings of the upper and lower 
connection links on the forward and aft passenger/crew doors, and 
correction of discrepancies, if necessary. This proposal would also 
require replacement of the shouldered bushing on the locking mechanism 
with a new oversized bushing, which would terminate the repetitive 
inspection requirements. This proposal is prompted by a report that, 
during an emergency evacuation of in-service airplanes, the left aft 
passenger/crew door jammed against the fuselage structure in a nearly 
closed position due to bushing migration. The actions specified by the 
proposed AD are intended to prevent jamming of the passenger/crew door, 
which could delay or impede the evacuation of passengers during an 
emergency.

DATES: Comments must be received by October 25, 1994.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 94-NM-94-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: 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:

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 94-NM-94-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. 94-NM-94-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    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 certain Airbus Model A320 series 
airplanes. The DGAC advises that, during an emergency evacuation of an 
in-service airplane, the left aft passenger/crew door jammed against 
the fuselage structure in a nearly closed position. Investigation 
revealed the bushing of the lower connection link had migrated. The 
cause of this migration has been attributed to the seizing of the upper 
locking hook into its bronze bushing from the frame segment at the 
level of the door lifting bellcranks. This condition, if not corrected, 
could result in jamming of the passenger/crew door, which could delay 
or impede the evacuation of passengers during an emergency.
    Airbus has issued Service Bulletin A320-52-1047, dated April 25, 
1994, which describes procedures for:
    1. Performing repetitive detailed visual inspections to verify 
proper installation of the plain bushings of the upper and lower 
connection links on the forward and aft passenger/crew doors;
    2. Removing the passenger/crew door and inspecting the bushings to 
detect damage, if any bushing has migrated;
    3. Reinstalling the bushing, if the bushing housings are not 
damaged; and
    4. Reaming the door structure and installing an oversize shouldered 
bushing, if any bushing housing is damaged; and repairing the bushing 
housing, if damage is not completely removed.
    Airbus has also issued Service Bulletin A320-52-1027, Revision 3, 
dated December 10, 1993, which describes procedures for replacing the 
shouldered bushing on the locking mechanism with a new oversized 
bushing, which will prevent jamming of the passenger/crew door.
    The DGAC classified these service bulletins as mandatory and issued 
French Airworthiness Directive 93-207-048(B), dated December 8, 1993, 
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 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.
    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 repetitive detailed 
visual inspections to verify proper installation of the plain bushings 
of the upper and lower connection links on the forward and aft 
passenger/crew doors, and correction of discrepancies, if necessary. 
The proposed AD would also require replacement of the shouldered 
bushing on the locking mechanism with a new oversized bushing, which 
would terminate the repetitive inspection requirements. The actions 
would be required to be accomplished in accordance with the service 
bulletins described previously. Correction of certain discrepancies 
would be required to be accomplished in accordance with a method 
approved by the FAA.
    The FAA estimates that 99 airplanes of U.S. registry would be 
affected by this proposed AD. It would take approximately 72 work hours 
per airplane to accomplish the proposed modification at an average 
labor rate of $55 per work hour. Required parts would be supplied by 
the manufacturer at no cost to the operators. Based on these figures, 
the total cost impact of the modification proposed by this AD on U.S. 
operators is estimated to be $392,040, or $3,960 per airplane.
    It would take approximately 6 work hours per airplane to accomplish 
the proposed inspection at an average labor rate of $55 per work hour. 
Based on these figures, the total cost impact of the inspection 
proposed by this AD on U.S. operators is estimated to be $32,670, or 
$330 per airplane.
    Based on the above figures, the total cost impact of the inspection 
and modification proposed by this AD on U.S. operators is estimated to 
be $424,710, or $4,290 per airplane.
    The total 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 AD were not adopted.
    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. 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:

Airbus Industrie: Docket 94-NM-94-AD.

    Applicability: Model A320 series airplanes on which Airbus 
Modification 22422 (reference Airbus Service Bulletin A320-52-1027) 
has not been installed, certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent jamming of the passenger/crew door, which could delay 
or impede the evacuation of passengers during an emergency, 
accomplish the following:
    (a) Within 450 flight hours after the effective date of this AD, 
perform a detailed visual inspection to verify proper installation 
of the plain bushings of the upper and lower connection links on the 
forward and aft passenger/crew doors, in accordance with Airbus 
Service Bulletin A320-52-1047, dated April 25, 1994.
    (1) If all bushings are installed properly, repeat the 
inspection thereafter at intervals not to exceed 900 flight hours 
until the modification required by paragraph (b) of this AD is 
accomplished.
    (2) If any bushing has migrated, prior to further flight, remove 
the passenger/crew door and visually inspect the bushing to detect 
damage, in accordance with the service bulletin.
    (i) If the bushing housings are not damaged, prior to further 
flight, reinstall the bushing in accordance with the service 
bulletin. Repeat the detailed visual inspections thereafter at 
intervals not to exceed 450 flight hours until the modification 
required by paragraph (b) of this AD is accomplished.
    (ii) If any bushing housing is damaged, prior to further flight, 
ream the door structure and install an oversize shouldered bushing, 
in accordance with the service bulletin. If the damage is not 
completely removed after reaming, prior to further flight, repair 
the bushing housing in accordance with a method approved by the 
Manager, Standardization Branch, ANM-113, FAA, Transport Airplane 
Directorate.
    (b) Within 3,500 flight hours after the effective date of this 
AD, replace the shouldered bushing on the locking mechanism with a 
new oversized bushing (Kit No. 521027A02), in accordance with Airbus 
Service Bulletin A320-52-1027, Revision 2, dated February 18, 1993, 
or Revision 3, dated December 10, 1993. Accomplishment of this 
modification constitutes terminating action for the repetitive 
inspection requirements of this AD.
    (c) 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, 
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, 
Standardization Branch, ANM-113.

    Note: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Standardization Branch, ANM-113.

    (d) Special flight permits may be issued 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.

    Issued in Renton, Washington, on August 24, 1994.
N.B. Martenson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 94-21362 Filed 8-29-94; 8:45 am]
BILLING CODE 4910-13-U