[Federal Register Volume 66, Number 161 (Monday, August 20, 2001)]
[Rules and Regulations]
[Pages 43467-43471]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-20699]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-302-AD; Amendment 39-12376; AD 2001-16-08]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747 Series Airplanes 
Equipped With General Electric Model CF6-45 or -50 Series Engines or 
Pratt & Whitney Model JT9D-3, -7, or -70 Series Engines; and 747-E4B 
(Military) Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain Boeing Model 747 series airplanes equipped 
with General Electric Model CF6-45 or -50 series engines or Pratt & 
Whitney Model JT9D-3, -7, or -70 series engines; and all 747-E4B 
(military) airplanes. That AD currently requires repetitive inspections 
to detect cracking or fracture of the steel attachment fittings of the 
diagonal brace to the nacelle struts; and replacement of the attachment 
fittings with new steel fittings, if necessary. This amendment adds new 
repetitive inspections of the fasteners of the steel attachment 
fittings of the diagonal brace to the inboard and outboard nacelle 
struts to find discrepancies; and mandates certain one-time inspections 
of the existing attachment fittings, installation of new fasteners, and 
replacement or rework of the fittings, which terminates the repetitive 
inspections. This amendment is prompted by a report of fatigue cracking 
in a steel attachment fitting of the diagonal brace to the number 2 
nacelle strut. The actions specified by this AD are intended to prevent 
such cracking or a fracture, which could result in failure of a nacelle 
strut diagonal brace load path and possible separation of the nacelle 
from the wing.

DATES: Effective September 24, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 24, 2001.

ADDRESSES: The service information referenced in this AD may be 
obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, 
Washington 98124-2207. This information may be examined at the Federal 
Aviation Administration (FAA), Transport Airplane Directorate, Rules 
Docket, 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: Tamara L. Anderson, Aerospace 
Engineer, Airframe Branch, ANM-120S, Seattle Aircraft Certification 
Office, FAA, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; 
telephone (425) 227-2771; fax (425) 227-1181.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 99-09-11, 
amendment 39-11144 (64 FR 19883, April 23, 1999), which is applicable 
to certain Boeing Model 747 series airplanes and all 747-E4B (military) 
airplanes, was published in the Federal Register on March 29, 2001 (66 
FR 17091). The action proposed to continue to require repetitive 
inspections to detect cracking or fracture of the steel attachment 
fittings of the diagonal brace

[[Page 43468]]

to the nacelle struts; and replacement of the attachment fittings with 
new steel fittings, if necessary. The action proposed to add new 
repetitive inspections of the fasteners of the steel attachment 
fittings of the diagonal brace to the inboard and outboard nacelle 
struts to find discrepancies; and mandate certain one-time inspections 
of the existing attachment fittings, installation of new fasteners, and 
replacement or rework of the fittings, which would terminate the 
repetitive inspections.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Several comments were submitted by a 
single commenter, and the FAA has duly considered these comments.

Increase Cost Impact Estimate

    The commenter requests that the FAA revise the Cost Impact section 
of the proposed rule to increase its estimate of the number of work 
hours from 76 to 476 work hours for the proposed terminating action. 
The commenter states that 476 work hours is the estimate given for the 
terminating action in Boeing Service Bulletin 747-54A2196, Revision 1, 
dated August 17, 2000 (which is referenced as the appropriate source of 
service information for doing the terminating action in the proposed 
AD). The commenter states that it is appropriate to include the time 
necessary for access and close-up because the airplane's engines are 
not normally removed during a ``C''-check or heavy maintenance visit, 
but engine removal and re-installation are necessary for the 
terminating action in the proposed AD.
    The FAA concurs. We acknowledge that operators must remove the 
engines (and re-install them) to do the terminating action required by 
this AD, and that the airplane's engines may not normally be removed at 
a maintenance visit that will occur during the compliance times 
required by this AD. We find, though, that the commenter's estimate of 
476 work hours is less than the figure of 516 work hours, which the 
service bulletin provides. Therefore, we have revised the ``Cost 
Impact'' section of this final rule to estimate that the terminating 
action required by this AD will take 516 work hours (including time for 
gaining access and closing up).

Extend Compliance Time for New Inspection

    The commenter requests that the FAA revise paragraph (b) of the 
proposed AD to revise the compliance time from the latest of 3,000 
total flight cycles on any diagonal brace attachment fitting, within 30 
days after the effective date of the AD, and within 150 flight cycles 
after accomplishment of AD 95-10-16 or AD 95-13-07; to the earlier of 
18 months after the effective date of the AD and at the next ``C''-
check visit after the effective date of the AD. The commenter's 
rationale is that the repetitive inspections currently required by AD 
99-09-01 at the initial inspection threshold and repetitive interval 
required by that AD have been effective in ensuring that any 
extensively damaged or failed fittings are found and replaced in a 
timely manner. The commenter states that it presumes the existing 
inspections were sufficiently justified and determined to be adequate 
to maintain the necessary level of safety. The commenter also states 
that it views the proposed AD's more extensive inspections as 
supplementing rather than replacing the existing inspections required 
by AD 99-09-01. The commenter clarifies that, if the FAA grants its 
request, the repetitive inspections required by AD 99-09-01 should 
continue until the terminating action in the proposed AD is 
accomplished.
    The FAA does not concur with the commenter's request. In the 
preamble of AD 99-09-11, we stated that the actions required by that AD 
were considered to be ``interim action,'' and that further rulemaking 
was being considered. As stated in the proposed rule, since the 
issuance of AD 99-09-11, we have reviewed and approved Boeing Service 
Bulletin 747-54A2196, Revision 1. We have determined that the 
inspections in that service bulletin provide an increased level of 
safety over the detailed visual inspections required by AD 99-09-11. We 
have also received reports that, while doing the new inspections 
required by this AD, operators have found damaged fittings that would 
not have been found during the inspections required by AD 99-09-11. For 
these reasons, the FAA finds it appropriate to supersede the existing 
AD to require the new inspections at the compliance times specified in 
Boeing Service Bulletin 747-54A2196, Revision 1. Also note that we have 
approved that service bulletin (as well as the original issue, dated 
April 2, 1999) as an alternative method of compliance to AD 99-09-11. 
No change to the final rule is necessary in this regard.

Extend Compliance Time for Terminating Action

    The commenter requests that the FAA revise paragraph (h) of the 
proposed rule to extend the compliance time for the proposed 
terminating action from 36 months (after the effective date of the AD) 
for the diagonal brace to the inboard nacelle struts and 48 months 
(after the effective date of the AD) for the diagonal brace on the 
outboard nacelle struts, to 54 months. The commenter notes that the 
proposed compliance times allow the work involved with the terminating 
action on both the inboard and outboard nacelle struts to be spread out 
over only two ``C''-checks. The commenter also notes that there is a 
lead time of 270 days for obtaining the kit necessary for the 
terminating action. The commenter states that its recommendation of a 
54-month compliance time would allow the work to be spread over two 
``C''-checks and a partial ``D''-check and provide sufficient time to 
obtain the kit necessary for terminating action.
    The FAA does not concur with the commenter's request. In developing 
an appropriate compliance time for this AD, the FAA considered not only 
the manufacturer's recommendation, but also the criticality of the 
strut-to-wing attachments. The commenter did not submit any technical 
data showing that an extension of the compliance time for the 
terminating action to 54 months would provide an acceptable level of 
safety. Thus, the FAA does not find it appropriate to revise the 
compliance time as requested by the commenter. However, the commenter 
may submit a request for an adjustment of the compliance times in this 
AD according to paragraph (i)(1) of this AD. In its request, the 
operator may want to provide the number of subject airplanes in its 
fleet, the number of airplanes on which it has done the terminating 
action, and the schedule for doing the terminating action on the 
remaining airplanes. The FAA will consider an operator's good-faith 
attempt to complete the terminating action within the required 
compliance times. No change to the final rule is necessary in this 
regard.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes previously 
described. The FAA has determined that these changes will neither 
significantly increase the economic burden on any operator nor increase 
the scope of the AD.

Cost Impact

    There are approximately 745 Model 747 series airplanes of the 
affected design in the worldwide fleet. The FAA

[[Page 43469]]

estimates that 173 airplanes of U.S. registry will be affected by this 
AD.
    The inspections that are currently required by AD 99-09-11 take 
approximately 4 work hours 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 $41,520, or $240 per airplane, per inspection cycle.
    The new detailed visual inspections/torque checks that are required 
by this AD will take approximately 12 work hours per airplane to 
accomplish, at an average labor rate of $60 per work hour. Based on 
these figures, the cost impact of the inspections/torque checks 
required by this AD on U.S. operators is estimated to be $124,560, or 
$720 per airplane, per inspection cycle.
    The new terminating actions (which include, for the inboard pylon, 
inspection of the existing steel fittings for cracks or damage; 
replacement if cracked; rework or replacement if damaged; or 
installation of new fasteners if no cracks; and, for the outboard 
pylon, detailed visual inspection of the fitting for damage, high 
frequency eddy current inspection of fastener holes, and installation 
of new fasteners) required by this AD will take approximately 516 work 
hours per airplane (including time for gaining access and closing up) 
to accomplish, at an average labor rate of $60 per work hour. Required 
parts will cost $13,776 (for airplanes equipped with Pratt & Whitney 
JT9D series engines) or $31,083 (for airplanes equipped with GE CF6-45 
or -50 series engines). Based on these figures, the cost impact of the 
terminating actions required by this AD is estimated to be $44,736 per 
airplane (for airplanes equipped with Pratt & Whitney JT9D series 
engines) or $62,043 per airplane (for airplanes equipped with General 
Electric CF6-45 or -50 series engines).
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the 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 usually represent only the time necessary to 
perform the specific actions actually required by the AD. While the 
cost impact figures given above for the terminating actions include 
time for gaining access and closing up, cost impact figures in AD 
rulemaking actions 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 adopted herein will 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 final rule does not have federalism 
implications under Executive Order 13132.
    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 removing amendment 39-11144 (64 FR 
19883, April 23, 1999), and by adding a new airworthiness directive 
(AD), amendment 39-12376, to read as follows:

2001-16-08  Boeing: Amendment 39-12376. Docket 2000-NM-302-AD. 
Supersedes AD 99-09-11, Amendment 39-11144.

    Applicability: Model 747 series airplanes equipped with General 
Electric Model CF6-45 or -50 series engines or Pratt & Whitney Model 
JT9D-3, -7, or -70 series engines; and all 747-E4B (military) 
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 per paragraph (i)(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 fatigue cracking or fracture of the steel attachment 
fittings of the diagonal brace to the nacelle struts, which could 
result in failure of a nacelle strut diagonal brace load path and 
possible separation of the nacelle from the wing, accomplish the 
following:

Restatement of Requirements of AD 99-09-11

Repetitive Inspections

    (a) Gain access to the attachment fittings of the diagonal brace 
to the inboard and outboard nacelle struts through the aft fairing 
doors, and do a detailed visual inspection to find cracking or 
fracture of the steel attachment fittings of the diagonal brace to 
the inboard and outboard nacelle struts, at the applicable time 
specified in paragraph (a)(1) or (a)(2) of this AD.
    (1) For airplanes on which the strut and wing modification 
required by AD 95-10-16, amendment 39-9233, or AD 95-13-07, 
amendment 39-9287, has not been accomplished: Within 10 days after 
May 10, 1999 (the effective date of AD 99-09-11, amendment 39-
11144), accomplish the detailed visual inspection.
    (i) For airplanes equipped with General Electric Model CF6-45 or 
-50 series engines and/or Pratt & Whitney JT9D-3 or -7 series 
engines, repeat the inspection thereafter at intervals not to exceed 
180 flight cycles.
    (ii) For airplanes equipped with Pratt & Whitney JT9D-70 series 
engines, repeat the inspection thereafter at intervals not to exceed 
250 flight cycles.
    (2) For airplanes on which the strut and wing modification 
required by AD 95-10-16, or AD 95-13-07, has been accomplished: 
Within 30 days after May 10, 1999, or within 150 flight cycles after 
accomplishment of the modification, whichever occurs later, 
accomplish the detailed visual inspection.
    (i) For airplanes equipped with General Electric Model CF6-45 or 
-50 series engines or Pratt & Whitney JT9D-70 series engines, repeat 
the inspection thereafter at intervals not to exceed 600 flight 
cycles.
    (ii) For airplanes equipped with Pratt & Whitney JT9D-3 or -7 
series engines, repeat the inspection thereafter at intervals not to 
exceed 350 flight cycles.

[[Page 43470]]

New Requirements of This AD:

Initial/Repetitive Inspections/Checks

    (b) For all airplanes: Do a detailed visual inspection and a 
torque check of the fasteners of the steel attachment fittings of 
the diagonal brace to the inboard and outboard nacelle struts to 
find discrepancies (including cracks, loose or broken fasteners, 
etc.), at the latest of the times specified in paragraphs (b)(1), 
(b)(2), and (b)(3) of this AD; per Part 2 of the Accomplishment 
Instructions of Boeing Service Bulletin 747-54A2196, Revision 1, 
dated August 17, 2000. Repeat the inspections/checks thereafter as 
specified in paragraph (c) of this AD. Accomplishment of the 
inspections/checks specified in this paragraph terminates the 
inspections required by paragraph (a) of this AD.
    (1) Before the accumulation of 3,000 total flight cycles on any 
diagonal brace attachment fitting.
    (2) Within 30 days after the effective date of this AD.
    (3) Within 150 flight cycles after accomplishment of AD 95-10-16 
or AD 95-13-07.

    Note 2: For the purposes of this AD, a detailed visual 
inspection is defined as: ``An intensive visual examination of a 
specific structural area, system, installation, or assembly to 
detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at 
intensity deemed appropriate by the inspector. Inspection aids such 
as mirror, magnifying lenses, etc., may be used. Surface cleaning 
and elaborate access procedures may be required.''


    Note 3: Detailed visual inspections and torque checks 
accomplished before the effective date of this AD per Boeing Alert 
Service Bulletin 747-54A2196, dated April 2, 1999, are considered 
acceptable for compliance with the inspections/checks specified in 
paragraph (b) of this AD.

    (c) Except as provided by paragraph (d) of this AD: Repeat the 
detailed visual inspection required by paragraph (b) of this AD, as 
specified in Table 1 of this AD. Repeat the torque check required by 
paragraph (b) of this AD at intervals not to exceed 18 months. 
Repeat the inspections/checks until accomplishment of paragraph (h) 
of this AD. Table 1 follows:

        Table 1.--Repetitive Detailed Visual Inspection Intervals
------------------------------------------------------------------------
                                   For airplanes in   Then repeat at the
             For the                     group            earlier of
------------------------------------------------------------------------
(1) Inboard nacelle struts......  (i) 1 or 4........  Intervals not to
                                                       exceed 350 flight
                                                       cycles or 18
                                                       months.
                                  (ii) 2, 3, or 5...  Intervals not to
                                                       exceed 600 flight
                                                       cycles or 18
                                                       months.
------------------------------------------------------------------------
(2) Outboard nacelle struts.....  (i) 1, 2, or 4....  Intervals not to
                                                       exceed 350 flight
                                                       cycles or 18
                                                       months.
                                  (ii) 3 or 5.......  Intervals not to
                                                       exceed 600 flight
                                                       cycles or 18
                                                       months.
------------------------------------------------------------------------

    (d) For the attachment fittings of the diagonal brace to the 
inboard nacelle struts only: Instead of doing the repetitive 
detailed visual inspections per paragraph (c) of this AD, before 
further flight following the inspections required by paragraph (b) 
of this AD, do an ultrasonic inspection of the fasteners of the 
steel attachment fittings to find discrepancies, per Part 4 of the 
Accomplishment Instructions of Boeing Service Bulletin 747-54A2196, 
Revision 1, dated August 17, 2000.
    (1) Repeat the ultrasonic inspection at intervals not to exceed 
1,200 flight cycles, until accomplishment of paragraph (h) of this 
AD.
    (2) Repeat the detailed visual inspection and torque check 
required by paragraph (b) of this AD at intervals not to exceed 18 
months, until accomplishment of paragraph (h) of this AD.

Corrective Actions

    (e) If any crack indication is found during any inspection/check 
required by this AD, before further flight, verify the indication 
per Part 3 or Part 4 of the Accomplishment Instructions of Boeing 
Service Bulletin 747-54A2196, Revision 1, dated August 17, 2000, as 
applicable. If any cracking is verified, before further flight, 
replace the fasteners with new fasteners, and rework or replace the 
fitting, as applicable, per Part 5 of the Accomplishment 
Instructions of Boeing Service Bulletin 747-54A2196, Revision 1, 
dated August 17, 2000; which terminates the repetitive inspections 
required by this AD. Where the service bulletin specifies that the 
manufacturer may be contacted for disposition of certain repair 
actions, this AD requires such repair to be done per a method 
approved by the Manager, Seattle Aircraft Certification Office 
(ACO), FAA; or per data meeting the type certification basis of the 
airplane approved by a Boeing Company designated engineering 
representative (DER) who has been authorized by the Manager, Seattle 
ACO, to make such findings. For a repair method to be approved by 
the Manager, Seattle ACO, as required by this paragraph, the 
Manager's approval letter must specifically reference this AD.
    (f) If any loose or broken fastener is found during any 
inspection/check required by this AD, before further flight, do a 
high frequency eddy current inspection of the fastener hole to find 
cracking or damage, per Figure 6 of the Accomplishment Instructions 
of Boeing Service Bulletin 747-54A2196, Revision 1, dated August 17, 
2000. If no cracking or damage is found, before further flight, 
oversize the fastener hole and install a new fastener per Part 5 of 
the Accomplishment Instructions of the service bulletin. If any 
cracking or damage is found, before further flight, repair per a 
method approved by the Manager, Seattle ACO, or per data meeting the 
type certification basis of the airplane approved by a Boeing 
Company DER who has been authorized by the Manager, Seattle ACO, to 
make such findings. For a repair method to be approved by the 
Manager, Seattle ACO, as required by this paragraph, the Manager's 
approval letter must specifically reference this AD.
    (g) If any discrepancy of any attachment fitting is detected 
during any inspection/check required by this AD, before further 
flight, replace the fitting with a new steel fitting per a method 
approved by the Manager, Seattle ACO, or per data meeting the type 
certification of the airplane approved by a Boeing Company DER who 
has been authorized by the Manager, Seattle ACO, to make such 
findings. For a repair method to be approved by the Manager, Seattle 
ACO, as required by this paragraph, the Manager's approval letter 
must specifically reference this AD.

Terminating Action

    (h) Do the terminating action (for the inboard nacelle struts, 
includes inspection of the existing steel fittings for cracks or 
damage and replacement if cracked, rework or replacement if damaged, 
or installation of new fasteners if no cracks; for the outboard 
nacelle struts, includes a detailed visual inspection of the fitting 
for damage, HFEC inspection of fastener holes, and installation of 
new fasteners), per Part 5 of the Accomplishment Instructions of 
Boeing Service Bulletin 747-54A2196, Revision 1, dated August 17, 
2000, at the times specified in paragraph (h)(1) or (h)(2) of this 
AD, as applicable. Accomplishment of the actions specified in this 
paragraph constitutes terminating action for the repetitive detailed 
visual inspections/torque checks specified in paragraph (c) of this 
AD.
    (1) For steel attachment fittings of the diagonal brace to the 
inboard nacelle struts: Within 36 months after the effective date of 
this AD.
    (2) For steel attachment fittings of the diagonal brace to the 
outboard nacelle struts: Within 48 months after the effective date 
of this AD.

Alternative Methods of Compliance

    (i)(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, Seattle ACO. Operators shall submit 
their requests through an appropriate FAA Principal Maintenance 
Inspector, who may add comments and then send it to the Manager, 
Seattle ACO.
    (2) Alternative methods of compliance, approved previously per 
AD 99-09-11, amendment 39-11144, are approved as alternative methods 
of compliance with this AD.


[[Page 43471]]


    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Seattle ACO.

Special Flight Permits

    (j) 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.

Incorporation by Reference

    (k) Except as provided by paragraphs (a), (e), (f), and (g) of 
this AD; the actions shall be done in accordance with Boeing Service 
Bulletin 747-54A2196, Revision 1, dated August 17, 2000. 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 Boeing Commercial Airplane Group, 
P.O. Box 3707, Seattle, Washington 98124-2207. 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.

Effective Date

    (l) This amendment becomes effective on September 24, 2001.

    Issued in Renton, Washington, on August 10, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-20699 Filed 8-17-01; 8:45 am]
BILLING CODE 4910-13-P