[Federal Register Volume 65, Number 183 (Wednesday, September 20, 2000)]
[Proposed Rules]
[Pages 56814-56817]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-24116]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-381-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).

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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 repetitive 
inspections to detect wear of the inboard flap trunnions, and to detect 
wear or debonding of the protective half-shells; and corrective 
actions, if necessary. This proposal would require accomplishment of 
the previously optional terminating action. 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 intended to prevent chafing and resultant wear damage 
on the inboard flap drive trunnions or on the protective half-shells, 
which could result in failure of the trunnion primary load path; this 
would adversely affect the fatigue life of the secondary load path and 
could lead to loss of the flap.

DATES: Comments must be received by October 20, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 99-NM-381-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 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. 99-NM-381-AD'' in the subject line and need not be 
submitted in triplicate. Comments sent via the Internet as attached 
electronic files must 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: 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:

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.
    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 notice

[[Page 56815]]

must submit a self-addressed, stamped postcard on which the following 
statement is made: ``Comments to Docket Number 99-NM-381-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 No. 99-NM-381-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On August 10, 1999, the FAA issued AD 99-17-11, amendment 39-11259 
(64 FR 45868, August 23, 1999), applicable to certain Airbus Model 
A319, A320, and A321 series airplanes, to require repetitive 
inspections to detect wear of the inboard flap trunnions, and to detect 
wear or debonding of the protective half-shells; and corrective 
actions, if necessary. That action was prompted by issuance of 
mandatory continuing airworthiness information by a foreign civil 
airworthiness authority. The requirements of that AD are intended to 
detect and correct chafing and resultant wear damage on the inboard 
flap drive trunnions or on the protective half-shells, which could 
result in failure of the trunnion primary load path; this would 
adversely affect the fatigue life of the secondary load path and could 
lead to loss of the flap.

Actions Since Issuance of Previous Rule

    AD 99-17-11 provides for an optional modification, which, if 
accomplished, would constitute terminating action for the required 
inspections. Since the issuance of that AD, the FAA has determined that 
the modification should be made mandatory for airplanes subject to the 
identified unsafe condition. Such modification would terminate the 
extensive repetitive inspections and/or corrective actions of the 
protective half-shell (area 1) to detect wear or debonding, and of the 
trunnion (area 2) to detect wear.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletin A320-27-1117, Revision 02, dated 
January 18, 2000, which describes procedures for modification of the 
sliding panel mechanism of the flap drive trunnion. Revision 02 is 
essentially equivalent to previous revisions of the service bulletin 
(which were cited in AD 99-17-11 as appropriate sources of service 
information for accomplishment of the modification). However, certain 
work procedures have been clarified in Revision 02. Accomplishment of 
this modification would eliminate the need for repetitive inspections. 
The DGAC approved this service bulletin and issued French airworthiness 
directive 1996-271-092(B) R3, dated August 11, 1999, in order to assure 
the continued airworthiness of these airplanes in France.
    Airbus also has issued Service Bulletin A320-27-1108, Revision 04, 
dated November 22, 1999, which describes procedures for repetitive 
detailed visual inspections of the protective half-shell (area 1) to 
detect wear or debonding, and detailed visual inspections of the 
trunnion (area 2) to detect wear. This revision is essentially 
equivalent to previous revisions, which were cited as the appropriate 
sources of service information for certain inspections required by AD 
99-17-11. However, certain references have been revised and certain 
work procedures have been clarified in this revision.
    Airbus also has issued Service Bulletin A320-27-1066, Revision 5, 
dated June 25, 1999, which describes procedures for repetitive detailed 
visual inspections of areas 1 and 2 of the inboard flap trunnion to 
detect wear on the trunnion; and repair or replacement of the trunnion, 
if necessary. Revision 5 is essentially equivalent to A320-27-1066, 
Revision 4, dated July 15, 1997 (for Model A320 series airplanes), 
which was cited as an appropriate source of service information for 
certain inspections required by AD 99-17-11.

FAA's Conclusions

    These airplane models are manufactured in France and are 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 99-17-11 to 
continue to require the actions specified in that AD, and to require 
accomplishment of the previously optional terminating action. The 
actions would be required to be accomplished in accordance with the 
service bulletins described previously.
    The proposed AD also would revise paragraph (a)(3) of the existing 
AD to clarify which airplanes are affected by that paragraph. As stated 
in that paragraph, Airbus Model A320 series airplanes ``on which Airbus 
Modification 22881 has been accomplished, and on which Airbus 
Modification 22841 or the modification specified in Airbus Service 
Bulletin A320-27-1050 has not been accomplished'' should accomplish 
certain actions. Since Airbus Modification 22881 corresponds to Airbus 
Service Bulletin A320-27-1050, the statement is contradictory as 
written, and cannot be literally complied with by operators. Therefore, 
the FAA is revising paragraph (a)(3) to apply to Airbus Model A320 
series airplanes ``on which Airbus Modification 22881 (Airbus Service 
Bulletin A320-27-1050) has been accomplished, and on which Airbus 
Modification 22841 has not been accomplished.'' Paragraph (a)(3) has 
also been revised to provide operators with additional time in which to 
accomplish the inspection required by that paragraph. In addition, NOTE 
2 of this proposed AD explains the revision to paragraph (a)(3) of AD 
99-17-11 to correct the description of airplanes affected by that 
paragraph.

Differences Between Proposed Rule and Foreign AD

    The proposed AD would differ from the parallel French airworthiness 
directive in that it would mandate the accomplishment of the 
terminating action for the repetitive inspections. The French 
airworthiness directive provides for that action as optional. Mandating 
the terminating action is based on the FAA's determination that long-
term continued operational safety will be better assured by 
modifications or design changes to remove the source of the problem, 
rather than by repetitive inspections. Long-term inspections may not be 
providing the degree of safety assurance necessary for the transport 
airplane fleet. This, coupled with a better understanding of the human 
factors associated with numerous continual inspections, has led the FAA 
to consider placing less emphasis on inspections and more emphasis on 
design improvements. The proposed modification requirement is 
consistent with these conditions.

[[Page 56816]]

Cost Impact

    There are approximately 132 airplanes of U.S. registry that would 
be affected by this proposed AD.
    The actions that are currently required by AD 99-17-11, and 
retained in this AD, 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 $7,920, or $60 per airplane, per 
inspection cycle.
    The new actions that are proposed in this AD action would take 
approximately 14 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Required parts would be provided by 
the manufacturer at no cost to the operators. Based on these figures, 
the cost impact of the proposed requirements of this AD on U.S. 
operators is estimated to be $110,880, or $840 per airplane.
    The cost impact figures discussed above are 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 cost impact figures 
discussed in AD rulemaking actions represent only the time necessary to 
perform the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

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 39-11259 (64 FR 
45868, September 27, 1999), and by adding a new airworthiness directive 
(AD), to read as follows:

Airbus Industrie: Docket 99-NM-381-AD. Supersedes AD 99-17-11, 
Amendment 39-11259.

    Applicability: Model A319, A320, and A321 series airplanes; 
certificated in any category; except airplanes on which Airbus 
Modification 26495 (reference Airbus Service Bulletin A320-27-1117) 
has been accomplished.

    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 (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 chafing and resultant wear damage on the inboard flap 
drive trunnions or on the protective half-shells, which could result 
in failure of the trunnion primary load path, adversely affect the 
fatigue life of the secondary load path, and lead to loss of the 
flap, accomplish the following:

Restatement of Certain Requirements of AD 99-17-11

Inspections

    (a) For airplanes on which a protective half-shell has been 
installed over area 1 of the left or right inboard flap trunnion: 
Perform a detailed visual inspection of the protective half-shell 
(area 1) to detect wear or debonding, and perform a detailed visual 
inspection of the trunnion (area 2) to detect wear at the time 
specified in paragraph (a)(1), (a)(2), or (a)(3) of this AD, as 
applicable; in accordance with Airbus Service Bulletin A320-27-1108, 
Revision 01, dated July 15, 1997, Revision 02, dated April 17, 1998, 
or Revision 03, dated June 25, 1999.
    (1) For Model A319 and Model A320 series airplanes on which 
Airbus Modification 22841 has been installed: Inspect prior to the 
accumulation of 2,500 flight hours after the incorporation of the 
modification, or within 500 flight hours after September 27, 1999 
(the effective date of AD 99-17-11, amendment 39-11259), whichever 
occurs later.
    (2) For Model A321 series airplanes on which Airbus Modification 
23926 has been installed, or on which the repair specified in Airbus 
Service Bulletin A320-27-1097, dated October 5, 1996, or Revision 
01, dated July 15, 1997, has been accomplished; and for Model A320 
series airplanes on which the repair specified in Airbus Service 
Bulletin A320-27-1066, Revision 3, dated October 30, 1996, or 
Revision 4, dated July 15, 1997, has been accomplished: Inspect 
prior to the accumulation of 5,000 flight hours after incorporation 
of the repair or modification, or within 500 flight hours after 
September 27, 1999, whichever occurs later.
    (3) For Airbus Model A320 series airplanes on which Airbus 
Modification 22881 (Airbus Service Bulletin A320-27-1050) has been 
accomplished, and on which Airbus Modification 22841 has not been 
accomplished: Inspect within 500 flight hours after the effective 
date of this new AD.

    Note 2: Paragraph (a)(3) of AD 99-17-11 has been revised to 
correct the description of airplanes affected by that paragraph. 
Since such a revision could result in additional airplanes being 
affected, the compliance time has been restarted from the effective 
date of this AD to allow additional time to accomplish the actions 
required by that paragraph.

    (b) For airplanes on which no protective half-shell is installed 
over area 1 of the left or right inboard flap trunnion: Within 500 
flight hours after September 27, 1999, perform a detailed

[[Page 56817]]

visual inspection of areas 1 and 2 of the inboard flap trunnion to 
detect wear on the trunnion, in accordance with Airbus Service 
Bulletin A320-27-1066, Revision 4, dated July 15, 1997 (for Model 
A320 series airplanes); or A320-27-1097, Revision 01, dated July 15, 
1997, or Revision 02, dated June 25, 1999 (for Model A321 series 
airplanes).

Corrective Actions

    (c) Except as provided by paragraph (d) of this AD: Following 
the accomplishment of any inspection required by either paragraph 
(a) or (b) of this AD, perform the follow-on repetitive inspections 
and/or corrective actions, as applicable, in accordance with Airbus 
Service Bulletin A320-27-1066, Revision 4, dated July 15, 1997 (for 
Model A320 series airplanes); A320-27-1097, Revision 01, dated July 
15, 1997, or Revision 02, dated June 25, 1999 (for Model A321 series 
airplanes); or A320-27-1108, Revision 01, dated July 15, 1997, 
Revision 02, dated April 17, 1998, or Revision 03, dated June 25, 
1999 (for Model A319, A320, and A321 series airplanes); as 
applicable; at the compliance times specified in the applicable 
service bulletin.
    (d) If the applicable service bulletin specifies to contact 
Airbus for an appropriate action, prior to further flight, repair in 
accordance with a method approved by either the Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
or the Direction Generale de l'Aviation Civile (or its delegated 
agent).

New Requirements of This AD

Service Bulletin Revisions

    (e) As of the effective date of this new AD, the following 
service bulletin revisions must be used for accomplishment of the 
applicable actions required by paragraphs (a), (b), and (c) of this 
AD:
    (1) Airbus Service Bulletin A320-27-1108, Revision 04, dated 
November 22, 1999.
    (2) Airbus Service Bulletin A320-27-1066, Revision 5, dated June 
25, 1999.

Terminating Modification

    (f) Within 18 months after the effective date of this AD, modify 
the sliding panel driving mechanism of the flap drive trunnions, in 
accordance with Airbus Service Bulletin A320-27-1117, Revision 02, 
dated January 18, 2000. This modification constitutes terminating 
action for the repetitive inspections required by this AD.

    Note 3: Accomplishment of the modification required by paragraph 
(f) of this AD prior to the effective date of this AD in accordance 
with Airbus Service Bulletin A320-27-1117, dated July 31, 1997, or 
Revision 01, dated June 25, 1999, is acceptable for compliance with 
that paragraph.

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. 
Operators shall submit 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 99-17-11, amendment 39-11259, are approved as 
alternative methods of compliance with this AD.

    Note 4: 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 
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.

    Note 5: The subject of this AD is addressed in French 
airworthiness directive 1996-271-092(B) R3, dated August 11, 1999.


    Issued in Renton, Washington, on September 14, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-24116 Filed 9-19-00; 8:45 am]
BILLING CODE 4910-13-U