[Federal Register Volume 65, Number 135 (Thursday, July 13, 2000)]
[Proposed Rules]
[Pages 43265-43269]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-17758]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-243-AD]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model MD-11 and MD-
11F 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 McDonnell Douglas 
Model MD-11 and MD-11F series airplanes, that currently requires 
opening the circuit breaker of the pneumatic sense line heater tape, 
installing an inoperative ring, and coiling and stowing the electrical 
wire to the circuit breaker of the pneumatic sense line heater tape. 
That AD also provides for an optional inspection, which, if 
accomplished, constitutes terminating action for deactivation of the 
pneumatic sense line heater tape. This proposal is prompted by the 
FAA's determination that the one-time optional terminating inspection 
in the existing AD does not adequately detect chafing, electrical 
arcing, or inadequate

[[Page 43266]]

clearance of the subject area. The actions specified by the proposed AD 
are intended to detect and correct such inadequate clearance, which 
could result in a hole in the fuel feed pipe caused by electrical 
arcing, and consequent fuel leakage and possible ignition of the fuel 
vapors. This action would require repetitive inspections of the subject 
area and corrective actions, if necessary, and would provide for an 
optional terminating modification(s) for the repetitive inspection 
requirements.

DATES: Comments must be received by August 28, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 99-NM-243-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-243-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 Boeing Commercial Aircraft Group, Long Beach Division, 
3855 Lakewood Boulevard, Long Beach, California 90846, Attention: 
Technical Publications Business Administration, Dept. C1-L51 (2-60). 
This information may be examined at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the the 
FAA, Transport Airplane Directorate, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California.

FOR FURTHER INFORMATION CONTACT: Stephen Kolb, Senior Aerospace 
Engineer, Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft 
Certification Office, 3960 Paramount Boulevard, Lakewood, California 
90712; telephone (562) 627-5244; fax (562) 627-5210.

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 must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 99-NM-243-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-243-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On April 16, 1998, the FAA issued AD 98-08-11, amendment 39-10491 
(63 FR 20066, April 23, 1998), applicable to certain McDonnell Douglas 
Model MD-11 and MD-11F series airplanes, to require opening the circuit 
breaker of the pneumatic sense line heater tape, installing an 
inoperative ring, and coiling and stowing the electrical wire to the 
circuit breaker of the pneumatic sense line heater tape. That AD also 
provides for an optional inspection, which, if accomplished, 
constitutes terminating action for deactivation of the pneumatic sense 
line heater tape. That action was prompted by a report indicating that, 
while an airplane was on the ground, fuel was found leaking from the 
fuel feed pipe of the number 2 engine due to inadequate clearance 
between the fuel feed pipe and the pneumatic sense line heater tape. 
The requirements of that AD are intended to detect and correct such 
inadequate clearance, which could result in a hole in the fuel feed 
pipe caused by electrical arcing, and consequent fuel leakage and 
possible ignition of the fuel vapors.

Actions Since Issuance of Previous Rule

    Since the issuance of AD 98-08-11, the FAA has determined that the 
optional one-time inspection provided by that AD does not ensure 
adequate clearance between the heater tape of the pneumatic sense lines 
and fuel feed pipe of the number 2 engine, which could result in a hole 
in the fuel feed pipe caused by electrical arcing, and consequent fuel 
leakage and possible ignition of the fuel vapors. Because the pneumatic 
sense lines can move and cause the heater tape to contact the fuel feed 
pipe of the number 2 engine, the FAA finds that repetitive detailed 
visual inspections of the subject area are necessary in order to 
address the identified unsafe condition of this AD.

Explanation of Relevant Service Information

    The FAA has reviewed and approved McDonnell Douglas Alert Service 
Bulletin MD11-36A030, Revision 03, dated December 14, 1999. The alert 
service bulletin describes procedures for opening the circuit breaker 
of the pneumatic sense line heater tape, installing an inoperative 
ring, and coiling and stowing the electrical wire to the circuit 
breaker of the pneumatic sense line heater tape. Accomplishment of the 
above actions deactivates the pneumatic sense line heater tape. The 
alert service bulletin also describes procedures for repetitive 
detailed visual inspections to detect chafing, electrical arcing, or 
inadequate clearance of the heater tape of the pneumatic sense lines 
and fuel feed pipe of the number 2 engine; and corrective actions, if 
necessary. The corrective actions involve repositioning the pneumatic 
sense lines, rewrapping the insulation on the pneumatic sense lines, 
and repairing or replacing damaged parts with new parts. Accomplishment 
of the repetitive inspections eliminates the need for deactivation of 
the pneumatic sense line heater tape.
    The FAA also has reviewed and approved the following optional 
service bulletins. Accomplishment of the applicable actions specified 
in these service bulletins eliminates the need for

[[Page 43267]]

the repetitive inspections described above.
     McDonnell Douglas Service Bulletin MD11-36-018 R01, 
Revision 1, dated July 18, 1995, describes, for certain airplanes, 
procedures for modification of the high stage pilot valve located in 
the aft accessory compartment (including purging the sense lines and 
revising wiring of the high stage pilot valve).
     McDonnell Douglas Service Bulletin MD11-36-026, dated 
September 30, 1996, describes, for certain airplanes, procedures for 
disconnecting and splicing together the heater tape wires of the 
pneumatic sense lines for the high stage and fan air valves from the 
terminal strips in the lower vertical stabilizer.
     McDonnell Douglas Service Bulletin MD11-36-025 R01, 
Revision 01, dated July 31, 1997, describes, for certain airplanes, 
modification and reidentification of the pilot pressure regulator valve 
located in the aft accessory compartment (including purging the sense 
lines and revising the wiring of the pilot pressure regulator valve).
     McDonnell Douglas Service Bulletin MD11-36-028, dated 
December 7, 1998, describes, for certain airplanes, procedures for 
disconnecting the heater tape wires from their respective terminal 
strips and splicing the wire ends together.

Explanation of Requirements of Proposed Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same type design, the 
proposed AD would supersede AD 98-08-11 to require accomplishment of 
the actions specified in McDonnell Douglas Alert Service Bulletin MD11-
36A030, Revision 03, dated December 14, 1999, described previously. The 
proposed AD also would provide for an optional terminating modification 
for the repetitive inspection requirements. The proposed AD also would 
require that operators report results of inspection findings to the 
FAA.
    The FAA is not proposing to mandate the modification specified in 
paragraph (d)(1), (d)(2), (d)(3), or (d)(4) of this AD for several 
reasons:
    1. Accessing the pneumatic sense lines and fuel feed pipe of the 
number 2 engine for inspection is easily accomplished.
    2. The chafing, electrical arcing, or inadequate clearance of the 
subject area is easily detectable.
    3. The repetitive detailed visual inspections will minimize the 
probability of a hole in the fuel feed pipe being caused by electrical 
arcing, which may result in fuel leakage and possible ignition of the 
fuel vapor.

Differences Between the Proposed AD and Relevant Service 
Information

    Operators should note that, although McDonnell Douglas Alert 
Service Bulletin MD11-26A030 recommends accomplishing the repetitive 
detailed visual inspections at intervals not to exceed 5,000 flight 
hours, the FAA has determined that an interval of 5,000 flight hours or 
18 months, whichever occurs later, would address the identified unsafe 
condition in a timely manner. In developing an appropriate compliance 
time for this AD, the FAA considered not only the manufacturer's 
recommendation, but the degree of urgency associated with addressing 
the subject unsafe condition, the high utilization of some operator's 
affected fleet, and the time necessary to perform the inspection (one 
hour). In light of all of these factors, the FAA finds an interval of 
5,000 flight hours or 18 months, whichever occurs later, for the 
repetitive detailed visual inspections to be warranted, in that it 
represents an appropriate interval of time allowable for affected 
airplanes to continue to operate without compromising safety.
    In addition to the procedures described above, McDonnell Douglas 
Service Bulletin MD11-36-018 R01, Revision 1, describes procedures for 
modification of the high stage pilot valve of the left and right wings, 
and McDonnell Douglas Service Bulletin MD11-36-025 R01, Revision 01, 
describes procedures for modification and reidentification of the pilot 
pressure regulator valve of the left and right wings. Accomplishment of 
these modifications is not necessary to comply with certain optional 
actions provided by this AD. These particular modifications do not 
address the identified unsafe condition of this AD.

Cost Impact

    There are approximately 174 Model MD-11 and MD-11F series airplanes 
of the affected design in the worldwide fleet. The FAA estimates that 
67 airplanes of U.S. registry would be affected by this proposed AD.
    The modification that is currently required by AD 98-08-11, and 
retained in this proposed AD, takes 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 $4,020, or $60 per 
airplane.
    The new inspection that is proposed in this AD action would 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 new inspection proposed by this AD on U.S. operators is 
estimated to be $4,020, or $60 per airplane, per inspection cycle.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the current or proposed 
requirements of this AD action, and that no operator would accomplish 
those actions in the future if this AD were not adopted.
    Should an operator elect to accomplish the optional terminating 
action that would be provided by paragraph (d)(1) of this proposed AD, 
it would take approximately 4 work hours to accomplish it, at an 
average labor rate of $60 per work hour. The cost of required parts 
would be approximately $4,500 per airplane. Based on these figures, the 
cost impact of this optional terminating action would be $4,740 per 
airplane.
    Should an operator elect to accomplish the optional terminating 
action that would be provided by paragraph (d)(2) of this proposed AD, 
it would take approximately 1 work hour to accomplish it, at an average 
labor rate of $60 per work hour. The cost of required parts would be 
approximately $50 per airplane. Based on these figures, the cost impact 
of this optional terminating action would be $110 per airplane.
    Should an operator elect to accomplish the optional terminating 
action that would be provided by paragraph (d)(3) of this proposed AD, 
it would take approximately 2 work hours to accomplish it, at an 
average labor rate of $60 per work hour. The cost of required parts 
would be approximately $2,500 per airplane. Based on these figures, the 
cost impact of this optional terminating action would be $2,620 per 
airplane.
    Should an operator elect to accomplish the optional terminating 
action that would be provided by paragraph (d)(4) of this proposed AD, 
it would take approximately 4 work hours to accomplish it, at an 
average labor rate of $60 per work hour. The cost of required parts 
would be approximately $50 per airplane. Based on these figures, the 
cost impact of this optional terminating action would be $290 per 
airplane.

Regulatory Impact

    The regulations proposed herein would not have a substantial direct 
effect on the States, on the relationship

[[Page 43268]]

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 39-10491 (63 FR 
20066, April 23, 1998), and by adding a new airworthiness directive 
(AD), to read as follows:

McDonnell Douglas:  Docket 99-NM-243-AD. Supersedes AD 98-08-11, 
Amendment 39-10491.

    Applicability: Model MD-11 and MD-11F series airplanes, having 
manufacturer's fuselage numbers 0447 through 0552 inclusive, and 
0554 through 0620 inclusive; 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 (f) 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 inadequate clearance between the fuel feed 
pipe of the number 2 engine and the pneumatic sense line heater 
tape, which could result in a hole in the fuel feed pipe caused by 
electrical arcing, and consequent fuel leakage and possible ignition 
of the fuel vapors, accomplish the following:

Restatement of Requirements of AD 98-08-11

Modification

    (a) Within 7 days after April 28, 1998 (the effective date of AD 
98-08-11, amendment 39-10491), open the circuit breaker of the 
pneumatic sense line heater tape, install an inoperative ring, and 
coil and stow the electrical wire to the circuit breaker of the 
pneumatic sense line heater tape, in accordance with Phase 1 of the 
Accomplishment Instructions of McDonnell Douglas Alert Service 
Bulletin MD11-36A030, dated April 2, 1998; Revision 01, dated 
September 28, 1998; Revision 02, dated July 27, 1999; or Revision 
03, dated December 14, 1999. Accomplishment of these actions 
deactivates the pneumatic sense line heater tape.

    Note 2: The pneumatic sense line heater tape of the number 2 
engine has been deactivated. This deactivation may cause a nuisance 
shutdown of the bleed air system of the number 2 engine at top of 
descent.

New Requirements of This AD

Repetitive Inspections

    (b) Except as provided in paragraph (d) of this AD, within 6 
months after the effective date of this AD, perform a detailed 
visual inspection to detect chafing, electrical arcing, or 
inadequate clearance of the pneumatic sense lines and fuel feed pipe 
of the number 2 engine, in accordance with Phase 2 of the 
Accomplishment Instructions of McDonnell Douglas Alert Service 
Bulletin MD11-36A030, Revision 03, dated December 14, 1999. Repeat 
the inspection thereafter at intervals not to exceed 5,000 flight 
hours or 18 months, whichever occurs later. Accomplishment of the 
detailed visual inspection constitutes terminating action for the 
deactivation requirements of paragraph (a) of this AD.

    Note 3: 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 4: Detailed visual inspections accomplished before the 
effective date of this AD in accordance with McDonnell Douglas Alert 
Service Bulletin MD11-36A030, dated April 2, 1998, Revision 01, 
dated September 28, 1998, or Revision 02, dated July 27, 1999; are 
considered acceptable for compliance with the requirements of 
paragraph (b) of this AD.

Corrective Actions

    (c) If any discrepancy (i.e., as identified in Conditions 1, 2, 
3, 4, and 5 of the Accomplishment Instructions of McDonnell Douglas 
Alert Service Bulletin MD11-36A030, Revision 03, dated December 14, 
1999) is detected during any inspection required by paragraph (b) of 
this AD, before further flight, perform the applicable corrective 
actions in accordance with Conditions 1, 2, 3, 4, or 5 of the 
Accomplishment Instructions of McDonnell Douglas Alert Service 
Bulletin MD11-36A030, Revision 03, dated December 14, 1999, except 
as indicated in paragraphs (c)(1) and (c)(2) of this AD.
    (1) Accomplishment of the modification of the high stage pilot 
valve of the left and right wings in accordance with McDonnell 
Douglas Service Bulletin MD11-36-018 R01, Revision 1, dated July 18, 
1995, is NOT necessary to comply with the applicable corrective 
action in Condition 5 of the Accomplishment Instructions of the 
service bulletin.
    (2) Accomplishment of the modification and reidentification of 
the pilot pressure regulator valve of the left and right wings in 
accordance with McDonnell Douglas Service Bulletin MD11-36-025 R01, 
Revision 01, dated July 31, 1997, is NOT necessary to comply with 
the applicable corrective action in Condition 5 of the 
Accomplishment Instructions of the service bulletin.

Optional Actions

    (d) Accomplishment of the action(s) specified in paragraphs 
(d)(1), (d)(2), (d)(3), and (d)(4) of this AD, as applicable, 
constitutes terminating action for the repetitive inspection 
requirements of paragraph (b) of this AD.
    (1) For airplanes having manufacturer's fuselage numbers 0447 
through 0552 inclusive, and 0554

[[Page 43269]]

through 0573 inclusive: Before or in conjunction with the actions 
specified in paragraph (d)(2) of this AD, modify the high stage 
pilot valve located in the aft accessory compartment (including 
purging the sense lines and revising wiring of the high stage pilot 
valve), in accordance with McDonnell Douglas Service Bulletin MD11-
36-018 R01, Revision 1, dated July 18, 1995.

    Note 5: In addition to the procedures for modification of the 
high stage pilot valve located in the aft accessory compartment, 
McDonnell Douglas Service Bulletin MD11-36-018 R01, Revision 1, 
dated July 18, 1995, also describes procedures for modification of 
the high stage pilot valve of the left and right wings. 
Accomplishment of modification of the high stage pilot valve of the 
left and right wings is NOT necessary to comply with the optional 
action provided by paragraph (d)(1) of this AD.


    Note 6: Modification of the high stage pilot valve of the aft 
accessory compartment accomplished before the effective date of this 
AD in accordance with McDonnell Douglas Service Bulletin MD11-36-
018, dated March 28, 1995, is considered acceptable for compliance 
with the actions specified in paragraph (d)(1) of this AD.

    (2) For airplanes having manufacturer's fuselage numbers 0447 
through 0552 inclusive, and 0554 through 0608 inclusive: Disconnect 
and splice together the heater tape wires of the pneumatic sense 
lines for the high stage and fan air valves from the terminals 
strips in the lower vertical stabilizer, in accordance with 
McDonnell Douglas Service Bulletin MD11-36-026, dated September 30, 
1996.
    (3) For airplanes having manufacturer's fuselage numbers 0447 
through 0552 inclusive, and 0554 through 0608 inclusive: Before or 
in conjunction with the actions specified in paragraph (d)(4) of 
this AD, modify and reidentify the pilot pressure regulator valve 
located in the aft accessory compartment (including purging the 
sense lines and revising the wiring of the pilot pressure regulator 
valve), in accordance with McDonnell Douglas Service Bulletin MD11-
36-025 R01, Revision 01, dated July 31, 1997.

    Note 7: In addition to the procedures for modification and 
reidentification of the pilot pressure regulator valve located in 
the aft accessory compartment, McDonnell Douglas Service Bulletin 
MD11-36-025 R01, Revision 01, dated July 31, 1997, also describes 
procedures for modification and reidentification of the pilot 
pressure regulator valve of the left and right wings. Accomplishment 
of the modification and reidentification of the pilot pressure 
regulator valve of the left and right wings is not necessary to 
comply with the optional action provided by paragraph (d)(3) of this 
AD.


    Note 8: Modification and reidentification of the pilot pressure 
regulator valve of the aft accessory compartment accomplished before 
the effective date of this AD in accordance with McDonnell Douglas 
Service Bulletin MD11-36-025, dated February 14, 1997; is considered 
acceptable for compliance with the actions specified in paragraph 
(d)(3) of this AD.

    (4) For airplanes having manufacturer's fuselage numbers 0447 
through 0464 inclusive, 0466 through 0552 inclusive, and 0554 
through 0620 inclusive: Disconnect the heater tape wires from their 
respective terminal strips and splice the wire ends together, in 
accordance with McDonnell Douglas Service Bulletin MD11-36-028, 
dated December 7, 1998.

Reporting

    (e) Within 10 days after accomplishing any inspection required 
by paragraph (b) of this AD, submit a report of the inspection 
results (only negative findings) to the Manager, Los Angeles 
Aircraft Certification Office (ACO), FAA, Transport Airplane 
Directorate, 3960 Paramount Boulevard, Lakewood, California 90712-
4137; fax (562) 627-5210. Information collection requirements 
contained in this regulation have been approved by the Office of 
Management and Budget (OMB) under the provisions of the Paperwork 
Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been 
assigned OMB Control Number 2120-0056.

Alternative Methods of Compliance

    (f) 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, Los Angeles ACO. Operators shall 
submit their requests through an appropriate FAA Principal 
Maintenance Inspector, who may add comments and then send it to the 
Manager, Los Angeles ACO.

    Note 9: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Los Angeles ACO.

Special Flight Permits

    (g) 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.

    Issued in Renton, Washington, on July 7, 2000.
John J. Hickey,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-17758 Filed 7-12-00; 8:45 am]
BILLING CODE 4910-13-P