[Federal Register Volume 66, Number 163 (Wednesday, August 22, 2001)]
[Proposed Rules]
[Pages 44089-44093]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-21106]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-86-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2, A300 B4, A300 B4-
600, and A300 B4-600R Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Supplemental notice of proposed rulemaking; reopening of 
comment period.

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SUMMARY: This document revises an earlier proposed airworthiness 
directive (AD), applicable to all Airbus Model A300 B2 and A300 B4 
series airplanes, and all A300 B4-600, A300 B4-600R, and A300 F4-600R 
(collectively called A300-600) series airplanes. The original notice of 
proposed rulemaking (NPRM) would have required repetitive inspections 
for cracking of certain fittings, corrective action if necessary, and, 
for certain airplanes, a modification; and would have provided for 
optional terminating action for the repetitive inspections. That 
proposal was prompted by issuance of mandatory continuing airworthiness 
information by a foreign civil airworthiness authority. This 
supplemental NPRM revises the original NPRM by including additional 
variables for determination of the compliance times, allowing an 
optional repair for certain cracking conditions, and removing certain 
airplanes from the applicability. The actions specified by this new 
proposed AD are intended to detect and correct propagation of cracks on 
the frame 40 aft fittings due to local stress concentrations at the 
frame 40 upper flange runout, which could result in reduced structural 
integrity of the airplane.

DATES: Comments must be received by September 17, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 99-NM-86-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. 99-NM-86-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: 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

[[Page 44090]]

Docket Number 99-NM-86-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-86-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to add an airworthiness directive (AD), applicable to all 
Airbus Model A300 B2 and A300 B4 series airplanes, and all Model A300 
B4-600, A300 B4-600R, and A300 F4-600R (collectively called A300-600) 
series airplanes, was published as a notice of proposed rulemaking 
(NPRM) in the Federal Register on January 9, 2001 (66 FR 1612). That 
original NPRM would have required modifying the frame 40 aft fittings 
for certain airplanes. For all airplanes, the original NPRM would have 
required repetitive nondestructive test inspections to detect cracking 
of the frame 40 aft fittings, and corrective action if necessary; and 
would have provided for optional terminating action for the repetitive 
inspections. The original NPRM was prompted by reports that cracks were 
found on the frame 40 aft fittings at stringer 33 on the left and right 
sides of the fuselage; the cracks were caused by a local stress 
concentration at the frame 40 upper flange runout. That condition, if 
not corrected, could result in reduced structural integrity of the 
airplane.

Comments

    Due consideration has been given to comments received in response 
to the original NPRM.

Request To Include Flight Hours in Compliance Time Determination

    One commenter, the manufacturer, requests that flight hours also be 
included as a variable in the compliance time determination for the 
initial and repetitive inspections. The manufacturer and the FAA have 
agreed that both flight cycles and flight hours should be considered 
when determining the appropriate compliance threshold and repetitive 
interval for the inspections.
    The FAA concurs with the request, finding that this method of 
determining the compliance times will ensure an adequate level of 
safety. The compliance times in Table 3 of this supplemental NPRM have 
been revised accordingly.

Request To Allow Repair for Certain Conditions

    One commenter requests that the original NPRM be revised to allow 
rework of cracks in the aft fitting (in accordance with Airbus Service 
Bulletin A300-53-0296 or A300-53-6048) if the cracks are 10 mm or less 
in length. (The original NPRM would have required replacement of the 
cracked fitting.) The commenter considers that immediate replacement of 
a cracked fitting (in accordance with Airbus Service Bulletin A300-53-
0297 or A300-57-6053) for these smaller cracks is not economically 
acceptable.
    The FAA concurs. The FAA has determined that, for cracks that are 
10 mm or less in length, either reworking the cracked area or replacing 
the cracked fitting would be acceptable for affected airplanes to 
continue to safely operate until the next inspection. For cracks that 
are more than 10 mm in length, this supplemental NPRM would require 
either replacement of the cracked fitting in accordance with the 
applicable service bulletin referenced above, or a repair in accordance 
with a method approved by the FAA or the DGAC. These conditional 
actions based on crack length are consistent with those actions 
described in Service Bulletin A300-53-0296 or A300-53-6048. Therefore, 
this supplemental NPRM has been revised to simply state that repair 
would be required in accordance with those service bulletins. In light 
of the type of repair that would be required to address the identified 
unsafe condition, and in consonance with existing bilateral 
airworthiness agreements, the FAA has determined that, for this 
supplemental NPRM, a repair approved by either the FAA or the DGAC 
would be acceptable for compliance.

Request To Remove Certain Airplanes From Applicability

    One commenter requests that Model A300 F4-622R series airplanes be 
removed from the applicability of the original NPRM to correspond to 
the applicability of the revised parallel French airworthiness 
directive, which specifically excludes those airplanes because the 
actions proposed by this supplemental NPRM have been accomplished on 
those airplanes in production.
    The FAA concurs and has accordingly revised the applicability of 
this supplemental NPRM.

Request for Credit for Inspection

    Two commenters request that the proposed AD be revised to provide 
credit for an inspection already performed in accordance with the 
original issue of Airbus Service Bulletin A300-53-6048. (The original 
NPRM would have required compliance in accordance with Revision 01 or 
03, and would have provided credit for Revision 02.) The original issue 
of the parallel French airworthiness directive (1998-481-270(B)) was 
based on the original service bulletin.
    The FAA concurs. The actions specified by the original service 
bulletin do not vary significantly from those proposed in this 
supplemental NPRM. Note 2 of this supplemental NPRM has been revised to 
add credit for an inspection done in accordance with the original 
service bulletin.

Request To Change Sequence of Certain Actions

    One commenter suggests that the original NPRM be revised to change 
the sequence of the subparagraphs of paragraph (d) so that subparagraph 
(d)(3) immediately precedes paragraph (d)(1). The modification 
specified by Service Bulletins A300-53-0297 and A300-57-6053 cancels 
the inspection specified by Service Bulletins A300-53-0268 and A300-57-
6052; therefore, the commenter suggests that the corrective actions of 
paragraph (d) of the original NPRM list the inspection requirement 
before the modification requirement.
    The FAA agrees that the sequence of instructions as written in the 
original NPRM may be confusing. This supplemental NPRM has been revised 
to distinguish the terminating action as a separate action, which is 
included as new paragraph (e).

Request To Provide for Optional Terminating Action for Certain 
Conditions

    Two commenters request that the original NPRM be revised to provide 
for optional terminating action on Model A300 B4-600 and A300 B4-600R 
series airplanes if no cracks are found and no subsequent rework is 
required.
    The FAA partially concurs. Paragraph (b)(8) of the original NPRM 
does provide for Service Bulletin A300-57-6053 (and Airbus Service 
Bulletin A300-53-0297 for Model A300 B2 and A300 B4 series airplanes) 
as terminating action--whether cracks are found or not. However, the 
FAA agrees that clarification of the associated text in the original 
NPRM may be necessary. Therefore, paragraph (b)(8) and new paragraph 
(e) of this supplemental NPRM have been revised to clarify that the 
modification would terminate the proposed requirements, regardless of 
the inspection results.

[[Page 44091]]

Additional Change to Original NPRM

    Airbus Service Bulletin A300-53-6048, described previously, refers 
to Airbus Service Bulletin A300-53-6063 as an additional source of 
service information for accomplishment of certain repairs. New Note 3 
of this supplemental NPRM identifies this secondary reference.

Conclusion

    Since these changes expand the scope of the original NPRM, the FAA 
has determined that it is necessary to reopen the comment period to 
provide additional opportunity for public comment.

Cost Impact

    The FAA estimates that 70 airplanes of U.S. registry would be 
affected by this proposed AD.
    For affected airplanes, it would take approximately 92 work hours 
per airplane to accomplish the proposed modification, at an average 
labor rate of $60 per work hour. Required parts would cost as much as 
$874 per airplane. Based on these figures, the cost impact of the 
proposed modification is estimated to be as much as $6,394 per 
airplane.
    It would take approximately 10 work hours per airplane to 
accomplish the proposed inspection, at an average labor rate of $60 per 
work hour. Based on these figures, the cost impact of the proposed 
inspection on U.S. operators is estimated to be $42,000, or $600 per 
airplane, per inspection cycle.
    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 planning time, time 
required to gain access and close up, 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 adding the following new 
airworthiness directive:

Airbus Industrie: Docket 99-NM-86-AD.

    Applicability: All Model A300 B2, A300 B4, A300 B4-600, and A300 
B4-600R series airplanes; certificated in any category.

    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) 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 detect and correct propagation of cracks on the frame 40 aft 
fittings due to local stress concentrations at the upper flange 
runout of frame 40, which could result in reduced structural 
integrity of the airplane, accomplish the following:

Modification

    (a) For airplanes on which Airbus Modification 10430 has not 
been done before the effective date of this AD: Concurrently with 
the inspection required by paragraph (b) of this AD, modify the 
profile of frame 40 aft fittings per the service information 
specified in Table 1, as follows:

                                          Table 1.--Service Information
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                                   Do the actions in
            For model               accordance with      Of airbus service                   Dated
                                        either                bulletin
----------------------------------------------------------------------------------------------------------------
(1) A300 B2 and A300 B4 series    (i) Revision 01 or  A300-53-0296             September 30, 1998.
 airplanes.                       (ii) Revision 02..  A300-53-0296             May 12, 1999.
(2) A300 B4-600 and A300 B4-600R  (i) Revision 01 or  A300-53-6048             September 30, 1998.
 series airplanes.                (ii) Revision 03..  A300-53-6048             February 21, 2000.
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    Note 2: For Model A300 B4-600 and A300 B4-600R series airplanes: 
Actions performed in accordance with Airbus Service Bulletin A300-
53-6048, dated January 16, 1996; or Revision 02, dated May 12, 1999, 
are acceptable for compliance with the applicable requirements of 
this AD.


    Note 3: Airbus Service Bulletin A300-53-6048 refers to Airbus 
Service Bulletin A300-53-6063 as an additional source of service 
information for accomplishment of certain repairs.

Inspection

    (b) For all airplanes, inspect the airplane per Table 2, as 
follows:

[[Page 44092]]



                    Table 2.--Inspection Requirements
------------------------------------------------------------------------
           Requirements                          Description
------------------------------------------------------------------------
(1) Area to inspect...............  The frame 40 AFT fitting.
(2) Type of inspection............  Nondestructive test (NDT).
(3) Compliance time...............  As specified by paragraph (c) of
                                     this AD.
(4) Discrepancies to detect.......  Cracking.
(5) Service information...........  Inspect in accordance with the
                                     applicable service bulletin listed
                                     in Table 1 of this AD.
(6) Follow-on actions if you find   Repeat the inspection thereafter at
 no cracking.                        the applicable interval specified
                                     by Table 3 of this AD.
(7) Corrective actions if you find  Do the actions specified by
 cracking.                           paragraph (d) of this AD.
(8) Terminating action............  The modification specified by
                                     paragraph (e) of this AD terminates
                                     the requirements of this AD.
------------------------------------------------------------------------


    Note 4: An NDT per Part 6 53-15-30 procedure C of the NDT manual 
is also acceptable for compliance with the requirements of paragraph 
(b) of this AD.

    (c) Perform the inspection required by paragraph (b) of this AD 
per the schedule in Table 3 of this AD. For airplanes on which this 
inspection has been accomplished before the effective date of this 
AD, the initial compliance time may be extended by the repetitive 
interval following the date the inspection was accomplished. Table 3 
follows:

                                    Table 3.--Compliance Times for Inspection
----------------------------------------------------------------------------------------------------------------
                                         If the total flight
                                        cycles accumulated on                                 And repeat the
              For Model                 the airplane as of the        Then inspect         inspection at least
                                        effective date of this                                    every
                                                AD is
----------------------------------------------------------------------------------------------------------------
(1) A300 B4-600 and A300 B4-600R       (i) Fewer than 6,200...  Before the airplane      7,500 flight cycles or
 series airplanes, pre-Modification                              accumulates 7,700        17,250 flight hours,
 10430.                                                          total flight cycles or   whichever occurs
                                                                 17,710 total flight      first.
                                                                 hours, whichever
                                                                 occurs first.
                                       (ii) At least 6,200 and  Within 1,500 flight      7,500 flight cycles or
                                        fewer than 9,700.        cycles or 3,450 flight   17,250 flight hours,
                                                                 hours after the          whichever occurs
                                                                 effective date of this   first.
                                                                 AD, whichever occurs
                                                                 first.
                                       (iii) At least 9,700...  Within 750 flight        7,500 flight cycles or
                                                                 cycles or 1,725 flight   17,250 flight hours,
                                                                 hours after the          whichever occurs
                                                                 effective date of this   first.
                                                                 AD, whichever occurs
                                                                 first.
(2) A300 B4-600 and A300 B4-600R       (i) Fewer than 19,600..  Before the airplane      7,500 flight cycles, or
 series airplanes, post-Modification                             accumulates 21,100       17,250 flight hours,
 10430.                                                          total flight cycles or   whichever occurs
                                                                 48,530 total flight      first.
                                                                 hours, whichever
                                                                 occurs first.
                                       (ii) At least 19,600     Within 1,500 flight      7,500 flight cycles or
                                        and fewer than 23,100.   cycles or 3,450 flight   17,250 flight hours,
                                                                 hours after the          whichever occurs
                                                                 effective date of this   first.
                                                                 AD, whichever occurs
                                                                 first.
                                       (iii) At least 23,100..  Within 750 flight        7,500 flight cycles or
                                                                 cycles or 1,725 flight   17,250 flight hours,
                                                                 hours after the          whichever occurs
                                                                 effective date of this   first.
                                                                 AD, whichever occurs
                                                                 first.
(3) A300 B2 series airplanes.........  (i) Fewer than 12,000..  Before the airplane      5,500 flight cycles or
                                                                 accumulates 14,000       5,940 flight hours,
                                                                 total flight cycles or   whichever occurs
                                                                 15,120 total flight      first.
                                                                 hours, whichever
                                                                 occurs first.
                                       (ii) At least 12,000     Within 2,000 flight      5,500 flight cycles or
                                        and fewer than 17,000.   cycles or 2,160 flight   5,940 flight hours,
                                                                 hours after the          whichever occurs
                                                                 effective date of this   first.
                                                                 AD, whichever occurs
                                                                 first.
                                       (iii) At least 17,000..  Within 1,000 flight      5,500 flight cycles or
                                                                 cycles or 1,080 flight   5,940 flight hours,
                                                                 hours after the          whichever occurs
                                                                 effective date of this   first.
                                                                 AD, whichever occurs
                                                                 first.
(4) A300 B4-100 series airplanes.....  (i) Fewer than 9,500...  Before the airplane      4,500 flight cycles or
                                                                 accumulates 11,500       5,985 flight hours,
                                                                 total flight cycles or   whichever occurs
                                                                 15,295 total flight      first.
                                                                 hours, whichever
                                                                 occurs first.
                                       (ii) At least 9,500 and  Within 2,000 flight      4,500 flight cycles or
                                        fewer than 14,500.       cycles or 2,660 flight   5,985 flight hours,
                                                                 hours after the          whichever occurs
                                                                 effective date of this   first.
                                                                 AD, whichever occurs
                                                                 first.
                                       (iii) At least 14,500..  Within 1,000 flight      4,500 flight cycles or
                                                                 cycles or 1,330 flight   5,985 flight hours,
                                                                 hours after the          whichever occurs
                                                                 effective date of this   first.
                                                                 AD, whichever occurs
                                                                 first.
(5) A300 B4-200 series airplanes.....  (i) Fewer than 8,500...  Before the airplane      4,000 flight cycles or
                                                                 accumulates 10,500       8,320 flight hours,
                                                                 total flight cycles or   whichever occurs
                                                                 21,840 total flight      first.
                                                                 hours, whichever
                                                                 occurs first.
                                       (ii) At least 8,500 and  Within 2,000 flight      4,000 flight cycles or
                                        fewer than 13,500.       cycles or 4,160 flight   8,320 flight hours,
                                                                 hours after the          whichever occurs
                                                                 effective date of this   first.
                                                                 AD, whichever occurs
                                                                 first.
                                       (iii) At least 13,500..  Within 1,000 flight      4,000 flight cycles or
                                                                 cycles or 2,080 flight   8,320 flight hours,
                                                                 hours after the          whichever occurs
                                                                 effective date of this   first.
                                                                 AD, whichever occurs
                                                                 first.
----------------------------------------------------------------------------------------------------------------



[[Page 44093]]

    Note 5: An NDT inspection is also required by AD 98-25-07, 
amendment 39-10933, to be repetitively performed on Model A300 B4-
600 and A300 B4-600R series airplanes on which Airbus Modification 
10453 has not been installed. For those airplanes, if the inspection 
is done within the applicable compliance time specified by paragraph 
(c) of this AD, the threshold for the initial inspection of 
paragraph (b) of this AD may be extended by 1,500 flight cycles.

Corrective Actions

    (d) If any cracking is found during any inspection required by 
paragraph (b) of this AD: Except as required by paragraph (f) of 
this AD, prior to further flight, perform all applicable corrective 
actions in accordance with the applicable service bulletin 
identified in Table 1 of this AD.

Terminating Action

    (e) Accomplishment of the applicable modification specified by 
paragraph (e)(1) or (e)(2) of this AD terminates the requirements of 
this AD.
    (1) For Model A300 B4-600 and A300 B4-600R series airplanes: 
Perform the modification in accordance with Airbus Service Bulletin 
A300-57-6053, Revision 1, dated October 31, 1995; or Revision 02, 
dated June 2, 1999.
    (2) For Model A300 B2 and A300 B4 series airplanes: Perform the 
modification in accordance with Airbus Service Bulletin A300-53-
0297, Revision 2, dated October 31, 1995.

Exceptions to Service Bulletin Instructions

    (f) During any inspection required by this AD, if the service 
bulletin specifies to contact the manufacturer for an appropriate 
action: Prior to further flight, repair in accordance with a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the Direction Generale de l'Aviation 
Civile (DGAC) (or its delegated agent).

Alternative Methods of Compliance

    (g) 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 their requests through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, International Branch, ANM-116.

    Note 6: 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 7: The subject of this AD is addressed in French 
airworthiness directive 1998-481-270(B) R1, dated July 12, 2000.


    Issued in Renton, Washington, on August 15, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-21106 Filed 8-21-01; 8:45 am]
BILLING CODE 4910-13-P