[Federal Register Volume 62, Number 10 (Wednesday, January 15, 1997)]
[Rules and Regulations]
[Pages 2009-2011]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-538]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 96-NM-166-AD; Amendment 39-9880; AD 97-01-09]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A321 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), 
applicable to certain Airbus Model A321 series airplanes. This action 
requires repetitive inspections to detect cracking and delamination of 
the doors that contain the left and right emergency evacuation slides 
located at certain emergency exits; and repair or replacement, if 
necessary. This action also requires the accomplishment of a 
modification that serves as terminating action for the repetitive 
inspections. This amendment is prompted by a report indicating that a 
slide aboard an airplane deployed during flight and consequently 
separated from the airplane. The actions specified in this AD are 
intended to prevent the loss of these slides during flight, which could 
make certain exits unusable in the event of an emergency, and also 
damage the empennage.

DATES: Effective January 30, 1997.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of January 30, 1997.
    Comments for inclusion in the Rules Docket must be received on or 
before March 17, 1997.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No.96-NM-166-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: Charles Huber, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 
227-2589; fax (206) 227-1149.

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 certain Airbus 
Model A321 series airplanes. The DGAC advises that one operator of 
Model A321 series airplanes reported the loss of an emergency slide 
during flight. The airplane was climbing through flight level (FL) 200 
when a loud noise was heard; it was caused by an escape slide, located 
at the right Number 2 emergency exit, unfolding and floating in the 
airstream. After approximately five minutes, the slide was torn off the 
airplane and lost on ground.
    Visual inspection of the slide inflation system's bottle valve 
gauge revealed that the bottle had not discharged, thereby confirming 
that the slide inflation system had not been activated inadvertently. 
Further investigation revealed that the slide enclosure door (referred 
to commonly as the ``blow out door'') had been forced open, evidenced 
by the retained floating pin receptacles of the pneumatic ball locks 
(which are installed as a back-up device in the event that the 
pneumatic release fails).
    A subsequent inspection of other Model A321 series airplanes in the 
affected operator's fleet revealed:
    1. a blow out door that was damaged on the inside;
    2. snap buttons on slide packs that were open; and
    3. lacing cord on slide pack covers that was loosened.
    These findings established that the loss of the slide during flight 
was the result of either excessive internal pressure on the blow out 
door, or excessive pressure to the outside of this door due to an 
incorrectly adjusted boarding ramp or gangway. (The exit had been used 
to board passengers.)
    Deployment and separation of an emergency evacuation slides at 
emergency exits Number 2 or 3 during flight could make these exits 
unusable in the event of an emergency, and also could cause damage to 
the empennage.

Explanation of Relevant Service Information

    Airbus has issued All Operator Telex (AOT) 25-11, dated January 4, 
1996, and Revision 01, dated January 8, 1996. These documents describe 
procedures for conducting repetitive detailed visual and coin tap 
inspections to detect cracking and delamination of the left and right 
blow out doors at emergency exits Number 2 and 3.They also describe 
procedures for necessary repairs if

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either of these discrepancies are detected during an inspection. If 
cracking or delamination exceeds certain limits, the AOT's recommend 
replacement of the affected slide container with a serviceable 
container prior to further flight.
    The DGAC classified the AOT's as mandatory and issued French 
airworthiness directive (C/N) 96-054-078(B), dated March 13, 1996, in 
order to assure the continued airworthiness of these airplanes in 
France.
    Additionally, Airbus has issued Service Bulletin A320-25-1167, 
dated June 24, 1996, which describes a modification of the evacuation 
system at doors 2 and 3. (This service bulletin references Air Cruisers 
Service Bulletin S.B. 005-25-04, dated May 24, 1996, for additional 
procedural information.) Among other things, the modification entails:
    1. a revised packing procedure;
    2. relocating snaps on the lacing cover;
    3. installing longer lanyard straps; and
    4. replacing the frangible washers in the blow-out door with solid 
ring retainers.
    This modification will preclude the types of problems associated 
with the slide system that were previously experienced. The DGAC has 
classified this service bulletin as ``recommended.''

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 FederalAviation 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 the 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, this AD is being issued to prevent loss of an 
evacuation slide during flight. This AD requires repetitive visual and 
coin tap inspections to detect cracking and delamination of the blow 
out doors at emergency exits Number 2 and 3; and repair or replacement, 
as necessary. These actions are required to be accomplished in 
accordance with either of the Airbus AOT's described previously.
    This AD also requires the accomplishment of the modification of the 
escape slide system in accordance with Airbus Service Bulletin A320-25-
1167. This modification constitutes terminating action for the required 
repetitive inspections.

Differences Between the FAA's Action and the DGAC's Action

    Operators should note that this AD requires the modification of the 
escape slide system as terminating action for the inspections; whereas, 
the parallel French CN 96-054-078(B) does not require it. The adequacy 
of inspections needed to maintain the safety of the transport airplane 
fleet, coupled with a better understanding of the human factors 
associated with numerous repetitive inspections, has caused the FAA to 
place less emphasis on repetitive inspections and more emphasis on 
design improvements and material replacement. Thus, the FAA has decided 
to require, whenever practicable, modifications necessary to remove the 
source of the problem addressed. The modification requirement of this 
AD is in consonance with that decision.

Cost Impact

    None of the Airbus Model A321 series airplanes affected by this 
action are on the U.S. Register. All airplanes included in the 
applicability of this rule currently are operated by non-U.S. operators 
under foreign registry; therefore, they are not directly affected by 
this AD action. However, the FAA considers that this rule is necessary 
to ensure that the unsafe condition is addressed in the event that any 
of these subject airplanes are imported and placed on the U.S. Register 
in the future.
    Should an affected airplane be imported and placed on the U.S. 
Register in the future, it would require approximately 2 work hours to 
accomplish the required inspections, at an average labor charge of $60 
per work hour. Based on these figures, the cost impact of the 
inspection requirements of this AD would be $120 per airplane per 
inspection.
    Accomplishment of the required terminating modification would take 
approximately 5 work hours, at an average labor charge of $60 per work 
hour. Required parts cost would be provided at no charge to operators 
by the manufacturer of the slide system (Air Cruisers Company). Based 
on these figures, the cost impact of the modification requirements of 
this AD would be $300 per airplane.

Determination of Rule's Effective Date

    Since this AD action does not affect any airplane that is currently 
on the U.S. register, it has no adverse economic impact and imposes no 
additional burden on any person. Therefore, prior notice and public 
procedures hereon are unnecessary and the amendment may be made 
effective in less than 30 days after publication in the Federal 
Register.

Comments Invited

    Although this action is in the form of a final rule and was not 
preceded by notice and 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 96-NM-166-AD.'' The postcard will be date stamped and 
returned to the commenter.

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,

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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 adding the following new 
airworthiness directive:

97-01-09  Airbus: Amendment 39-9880. Docket 96-NM-166-AD.

    Applicability: Model A321 series airplanes; as listed in Airbus 
Industrie All Operator Telex (AOT) 25-11, Revision 01, dated January 
8, 1996, and Airbus Service Bulletin A320-25-1167, dated June 24, 
1996; on which Airbus Modification 25369 has not been installed; 
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 (c) 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 the loss of the left and right emergency evacuation 
slides at emergency exits Number 2 and 3 during flight, which could 
make these exits unusable in the event of an emergency and also 
could cause damage to the empennage, accomplish the following:
    (a) Within 500 hours time-in-service after the effective date of 
this AD, conduct a detailed visual inspection to detect cracking, 
and a coin tap inspection to detect delamination, of the left and 
right enclosure doors of the containers in which the emergency 
evacuation slides are packed (``the blow out doors'') at emergency 
exits Number 2 and 3, in accordance with Airbus Industrie All 
Operator Telex (AOT) 25-11, dated January 4, 1996; or Revision 01, 
dated January 8, 1996.
    (1) If no crack or delamination is detected, or if any crack or 
delamination is detected and it does not exceed 3 inches (75 mm) in 
length: Repeat the inspections thereafter at intervals not to exceed 
18 months.
    (2) If any crack or delamination is detected, and it is greater 
than 3 inches (75 mm) in length, but not greater than 10 inches (250 
mm) in length: Prior to further flight, repair the door in 
accordance with the AOT.
    (3) If any crack or delamination is detected, and it is greater 
than 10 inches (250 mm) in length: Prior to further flight, replace 
the door in accordance with the AOT.
    (b) Within 36 months after the effective date of this AD, modify 
the escape slide system in accordance with Airbus Service Bulletin 
A320-25-1167, dated June 24, 1996. Accomplishment of this 
modification constitutes terminating action for the repetitive 
inspections required by paragraph (a) of this AD.

    Note 2: Airbus Service Bulletin A320-25-1167 references Air 
Cruisers Service Bulletin S.B. 005-25-04, dated May 24, 1996, for 
additional procedural information.

    (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 3: 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 
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.
    (e) The inspections and repair shall be done in accordance with 
Airbus Industrie All Operator Telex 25-11, dated January 4, 1996; or 
Airbus Industrie All Operator Telex 25-11, Revision 01, dated 
January 8, 1996. The modification shall be done in accordance with 
Airbus Service Bulletin A320-25-1167, dated June 24, 1996. 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.
    (f) This amendment becomes effective on January 30, 1997.

    Issued in Renton, Washington, on January 3, 1997.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 97-538 Filed 1-14-97; 8:45 am]
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