[Federal Register Volume 66, Number 171 (Tuesday, September 4, 2001)]
[Proposed Rules]
[Pages 46243-46246]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-22090]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-413-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A319, A320, and A321 
Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD), applicable to certain Airbus Model A319, 
A320, and A321 series airplanes, that currently requires a one-time 
ultrasonic inspection to detect disbonding of the skin attachments at 
the stringers and spars of the vertical stabilizer, and repair, if 
necessary. For certain airplanes, that AD also requires prior or 
concurrent modification of the vertical stabilizer to ensure proper 
reinforcement of its attachment to the skin. This action would require 
ultrasonic inspections of the subject area, and repair, as necessary. 
It would also require installation of fasteners to reinforce the bonds 
to the skin, which would terminate the repetitive inspections. This 
proposal is prompted by issuance of mandatory continuing airworthiness 
information by a foreign civil airworthiness authority. The actions 
specified by the proposed AD are necessary to prevent failure of the 
bonds of the vertical stabilizer spar boxes to the skin, which could 
lead to reduced structural integrity of the spar boxes.

DATES: Comments must be received by October 4, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket Number 2000-NM-413-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. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2000-NM-413-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must

[[Page 46244]]

be formatted in Microsoft Word 97 for Windows or ASCII text.
    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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2125; 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 action may be changed in 
light of the comments received.
    Submit comments using the following format:
     Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
     For each issue, state what specific change to the proposed 
AD is being requested.
     Include justification (e.g., reasons or data) for each 
request.
    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 action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2000-NM-413-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-114, Attention: Rules 
Docket Number 2000-NM-413-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On June 2, 2000, the FAA issued AD 2000-11-27, amendment 39-11776 
(65 FR 37029, June 13, 2000), applicable to certain Airbus Model A319, 
A320, and A321 series airplanes, to require a one-time ultrasonic 
inspection to detect disbonding of the skin attachments at the 
stringers and spars of the vertical stabilizer, and repair, if 
necessary. For certain airplanes, that AD also requires prior or 
concurrent modification of the vertical stabilizer to ensure proper 
reinforcement of its attachment to the skin. That AD was prompted by 
reports received from the Direction Generale de l'Aviation Civile 
(DGAC), which is the airworthiness authority for France, of localized 
failure of bonds of the spars and stringers on several vertical 
stabilizer spar boxes to the skin. The failure resulted from 
contamination of the bonding surface during the production process. The 
requirements of that AD are intended to detect and correct disbonding 
of the vertical stabilizer structure, which could result in reduced 
structural integrity of the spar boxes of the vertical stabilizer.
    In the preamble of AD 2000-11-27, the FAA indicated that the 
actions required by that AD were considered to be interim action. 
Airbus had advised that it was then developing a program of repetitive 
inspections to address the localized disbonding. The FAA indicated that 
it might consider additional rulemaking once the repetitive inspection 
program had been developed, approved, and made available.
    Since the issuance of AD 2000-11-27, Airbus has developed a program 
for repetitive ultrasonic inspections of the bonds between the spars 
and stringers of the vertical stabilizer spar boxes and the skin. 
Airbus has also developed a program for installation of fasteners to 
reinforce the bond of the vertical stabilizers to the skin, which 
terminates the repetitive ultrasonic inspections. Airbus has 
incorporated these programs into the service bulletins described below.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletin A320-55A1027, Revision 02, dated 
February 13, 2001, which describes procedures for repetitive ultrasonic 
inspections of the spars and stringers of the vertical stabilizer spar 
box for failure of the bonds to the skin; and procedures for repair of 
localized areas of disbonding.
    Airbus has also issued Service Bulletin A320-55-1028, Revision 03, 
dated November 2, 2000, which describes procedures for installation of 
fasteners to reinforce those areas where the bond between the spars and 
stringers of the vertical stabilizer spar box and the skin are 
susceptible to failure. This installation terminates the repetitive 
inspections of the vertical stabilizer spar box.
    Accomplishment of the actions specified in these service bulletins 
is intended to adequately address the identified unsafe condition. The 
DGAC classified both service bulletins as mandatory and issued French 
airworthiness directive 2000-520-159(B), dated December 13, 2000, in 
order to assure the continued airworthiness of these airplanes in 
France.

FAA's Conclusions

    These airplane models are manufactured in France and are 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.

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 2000-11-27 to 
require repetitive ultrasonic inspection to detect disbonding of the 
skin attachments at the stringers and spars of the vertical stabilizer; 
and repair, if necessary. For certain airplanes, the proposed AD would 
continue to require prior or concurrent modification of the vertical 
stabilizer to ensure proper reinforcement of its attachment to the 
skin. The proposed AD would also require installation of fasteners to 
reinforce the bonds to the skin, which would constitute terminating 
action for

[[Page 46245]]

the repetitive inspections. The actions would be required to be 
accomplished in accordance with the service bulletins described 
previously.

Cost Impact

    There are approximately 23 airplanes of U.S. registry that would be 
affected by this proposed AD.
    The repetitive inspections that are proposed in this AD would take 
approximately 3 to 7 work hours per airplane to accomplish, at an 
average labor rate of $60 per work hour. Required parts would be 
provided by the airplane manufacturer at no cost to operators. Based on 
these figures, the cost impact on U.S. operators of the repetitive 
inspections proposed in this AD is estimated to be $4,140 to $9,660, or 
$180 to $420 per airplane, per inspection cycle.
    The installation of fasteners proposed in this AD would take 
approximately 5 to 480 work hours per airplane to accomplish, depending 
upon the configuration of the airplane, at an average labor rate of $60 
per work hour. Required parts would be provided by the airplane 
manufacturer at no cost to operators. Based on these figures, the cost 
impact on U.S. operators of the modification proposed in this AD is 
estimated to be $6,900 to $662,400, or $300 to $28,800 per airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the requirements of the 
proposed AD, 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 a substantial direct 
effect 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, it 
is determined that this proposal would not have federalism implications 
under Executive Order 13132.
    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 39-11776 (65 FR 
37029, June 13, 2000), and by adding a new airworthiness directive 
(AD), to read as follows:

Airbus Industrie: Docket 2000-NM-413-AD. Supersedes AD 2000-11-27, 
Amendment 39-11776.

    Applicability: Model A319, A320, and A321 series airplanes; 
certificated in any category; as listed in Airbus Service Bulletin 
A320-55A1027, dated May 13, 2000; Revision 01, dated August 1, 2000; 
or Revision 02, dated February 13, 2001, except those airplanes 
which have incorporated Modification No. 30432K6788, in accordance 
with Airbus Service Bulletin A320-55-1028, Revision 03, dated 
November 2, 2000.

    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 request approval for an 
alternative method of compliance in accordance with paragraph (g)(1) 
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 failure of the bonds of the vertical stabilizer spar 
box to the skin, which could lead to reduced structural integrity of 
the spar box, accomplish the following:

Restatement of Requirements of AD 2000-11-27

Ultrasonic Inspection

    (a) Within 60 days after June 28, 2000 (the effective date of AD 
2000-11-27, amendment 39-11776): Perform a one-time ultrasonic 
inspection to detect disbonding (damage) of the skin attachments the 
stringers and spars of the vertical stabilizer, left- and right-hand 
sides, in accordance with Airbus Service Bulletin A320-55A1027, 
dated May 13, 2000; Revision 01, dated August 1, 2000; or Revision 
02, dated February 13, 2001.

Modification (for Certain Airplanes)

    (b) For airplanes with manufacturer's serial numbers listed in 
paragraph B of the Planning Information of Airbus Service Bulletin 
A320-55A1027, dated May 13, 2000; Revision 01, dated August 1, 2000; 
or Revision 02, dated February 13, 2001: Prior to or concurrent with 
the ultrasonic inspection required by paragraph (a) of this AD, 
modify the vertical stabilizer to ensure proper reinforcement of the 
structure/skin attachments, in accordance with Airbus Service 
Bulletin A320-55-1026, Revision 01, dated May 20, 1999.

New Requirements of Proposed AD

Repetitive Inspections and Repair, If Necessary

    (c) Within 1,100 flight cycles from the previous inspection 
performed in accordance with paragraph (a) of this AD, or 60 days 
after the effective date of this AD, whichever occurs later: Perform 
an ultrasonic inspection to detect disbonding of the skin attachment 
at the spars and the stringers of the vertical stabilizer spar box, 
in accordance with Airbus Service Bulletin A320-55A1027, dated May 
13, 2000; Revision 01, dated August 1, 2000; or Revision 02, dated 
February 13, 2001.
    (d) If no damage is detected, or if only a single area of damage 
is found and it is less than or equal to an area of 300 square 
millimeters (mm\2\) during any ultrasonic inspection required by 
this AD, repeat the ultrasonic inspection thereafter at intervals 
not to exceed 1,100 flight cycles.
    (e) If any damage is detected and the area of damage found is 
greater than 300 mm\2\, or if multiple damage is found on one 
specific component (stringer/spar attachment) during any ultrasonic 
inspection required by this AD, prior to further flight, accomplish 
applicable repairs in accordance with Airbus Service Bulletin A320-
55A1027, dated May 13, 2000; Revision 01, dated August 1, 2000; or 
02, dated February 13, 2001. Repeat the ultrasonic inspection 
thereafter at intervals not to exceed 1,100 flight cycles.

Modification

    (f) Within 5 years after the date of manufacture of the 
airplane: Install fasteners to reinforce the attachment between the 
skin panel and areas of the vertical stabilizer affected by 
disbonding, in accordance with Airbus Service Bulletin A320-55-1028, 
Revision 03, dated November 2, 2000. Accomplishment of the 
installation terminates the repetitive inspections required by 
paragraph (c) of this AD.

Alternative Methods of Compliance

    (g)(1) 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,

[[Page 46246]]

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.
    (2) Alternative methods of compliance, approved previously in 
accordance with AD 2000-11-27, amendment 39-11776, are approved as 
alternative methods of compliance with paragraphs (a) and (b) of 
this AD.

    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.

Special Flight Permits

    (h) 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.

    Note 3: The subject of this AD is addressed in French 
airworthiness directive 2000-520-159(B), dated December 13, 2000.


    Issued in Renton, Washington, on August 27, 2001.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate Aircraft, Certification 
Service.
[FR Doc. 01-22090 Filed 8-31-01; 8:45 am]
BILLING CODE 4910-13-U