[Federal Register Volume 64, Number 6 (Monday, January 11, 1999)]
[Proposed Rules]
[Pages 1545-1549]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-482]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-318-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 737-100, -200, -300, -400, 
and -500 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 all Boeing Model 737-100, -
200, -300, -400, and -500 series airplanes, that currently requires 
removal of the fuel boost pump wiring in the conduits of the wing and 
center fuel tanks; an inspection to detect damage of the wiring, and 
corrective action, if necessary; and eventual installation of Teflon 
sleeving over the electrical cable. This action would expand the 
inspection requirement to include additional airplanes, add repetitive 
inspections for all airplanes, and reidentify the requirement to 
install Teflon sleeving as a nonterminating action. This proposal is 
prompted by the FAA's determination that Model 737-100 through -500 
series airplanes that are not affected by the current AD must also be 
protected against excessive wire chafing of the fuel boost pump wiring 
and that all affected airplanes must be repetitively inspected. The 
actions specified by the proposed AD are intended to detect and correct 
chafing and prevent electrical arcing between the fuel boost pump 
wiring and the surrounding conduit, which could result in arc-through 
of the conduit, and consequent fire or explosion of the fuel tank.

DATES: Comments must be received by February 25, 1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 98-NM-318-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056.

[[Page 1546]]

Comments may be inspected at this location between 9:00 a.m. and 3:00 
p.m., Monday through Friday, except Federal holidays.
    The service information referenced in the proposed rule may be 
obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, 
Washington 98124-2207. This information may be examined at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington.

FOR FURTHER INFORMATION CONTACT: Dorr Anderson, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Transport Airplane Directorate, 
Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056; telephone (425) 227-2684; fax (425) 227-1181.

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.
    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 98-NM-318-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. 98-NM-318-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On September 23, 1998, the FAA issued AD 98-19-09, amendment 39-
10751 (63 FR 52152, September 30, 1998), applicable to all Boeing Model 
737-100, -200, -300, -400, and -500 series airplanes, to require 
removal of the fuel boost pump wiring in the conduits of the wing and 
center fuel tanks; an inspection to detect damage of the wiring, and 
corrective action, if necessary; and eventual installation of Teflon 
sleeving over the electrical cable. The actions of that AD were 
required for airplanes that had accumulated 20,000 or more total flight 
hours. That AD was prompted by reports of severe wear of the fuel boost 
pump wiring due to chafing between the wiring and the surrounding 
conduit inside the fuel tank; pin-hole-sized holes in the conduit that 
appear to be the result of arc-through of the conduit; and exposure of 
the main tank boost pump wire conductor inside a conduit and signs of 
arcing to the wall of the conduit. The requirements of that AD are 
intended to detect and correct chafing and electrical arcing between 
the fuel boost pump wiring and the surrounding conduit, which, if not 
corrected, could result in arc-through of the conduit, and consequent 
fire or explosion of the fuel tank.

Actions Since Issuance of Previous Rule

    In the preamble to AD 98-19-09, the FAA indicated it was 
considering further rulemaking action to require inspection of Model 
737 series airplanes that have accumulated less than 20,000 total 
flight hours. The FAA now has determined that further rulemaking action 
is indeed necessary, and this proposed AD follows from that 
determination. The FAA has determined that it is necessary to expand 
the inspection requirement to ensure that excessive wire chafing does 
not occur on those airplanes.
    The FAA has examined wire bundles that were removed and inspected 
for chafing in accordance with telegraphic AD's T98-10-51 (issued on 
May 7, 1998) and T98-11-51 (issued on May 10, 1998) and AD 98-11-52 (63 
FR 34271, June 24, 1998). Based on the findings, the FAA tabulated 
levels of wire chafing as a function of airplane flight hours. Based on 
the tabulated data, the FAA has determined that it is necessary to 
define long-term repetitive inspection intervals to address the 
identified unsafe condition for the entire fleet of 737-100 through -
500 series airplanes. In consideration of these data and the additional 
layer of Teflon sleeving installed for further protection of the wire 
bundles, the FAA proposes a repetitive inspection interval of 30,000 
flight hours.
    In light of the new proposed repetitive inspections, the 
installation of Teflon sleeving required by AD 98-19-09, which 
terminates the requirements of that AD, would not terminate the 
requirements of this proposed AD.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Service Bulletin 737-
28A1120,
    Revision 2, dated November 26, 1998. The procedures described in 
Revision 2 of this service bulletin are essentially identical to those 
described in Boeing Alert Service Bulletin 737-28A1120, Revision 1, 
dated May 28, 1998 (which was referenced as an appropriate source of 
service information in AD 98-19-09). Revision 2 removes certain 
airplanes from the effectivity listing and specifies different parts to 
be provided in the parts kit by the manufacturer. Accomplishment of the 
actions specified in the service bulletin is intended to adequately 
address the identified unsafe condition.

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 98-19-09 to continue to require removal 
of the fuel boost pump wiring in the conduits of the wing and center 
fuel tanks; an inspection to detect damage of the wiring, and 
corrective action, if necessary; and eventual installation of Teflon 
sleeving over the electrical cable. This action would additionally 
require that the inspection be conducted at repetitive intervals and 
that the inspection be accomplished on airplanes that have accumulated 
less than 20,000 total flight hours. The actions would be required to 
be accomplished in accordance with the service bulletin described 
previously, except as discussed below. The proposed AD also would 
require that operators report results of the initial inspection to the 
FAA.

Difference Between the Proposed AD and the Service Bulletin

    Operators should note that, while Boeing Service Bulletin 737-
28A1120, Revision 2, limits its effectivity to airplanes having line 
numbers 1 through 3072 inclusive, this proposed AD would be applicable 
to all Model 737-100 through -500 series airplanes.

[[Page 1547]]

Cost Impact

    There are approximately 2,866 airplanes of the affected design in 
the worldwide fleet. The FAA estimates that 1,131 airplanes of U.S. 
registry would be affected by this proposed AD.
    The inspection that is currently required by AD 98-19-09, and 
retained in this AD, takes approximately 30 work hours per airplane to 
accomplish, at an average labor rate of $60 per work hour. This new AD 
action would require repetitive performance of that inspection. Based 
on these figures, the cost impact of the proposed AD on U.S. operators 
is estimated to be $2,035,800, or $1,800 per airplane, per inspection 
cycle.
    The cost impact figure discussed above is 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.

Regulatory Impact

    The regulations proposed herein would not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    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 39-10751 (63 FR 
52152, September 30, 1998), and by adding a new airworthiness directive 
(AD), to read as follows:
Boeing: Docket 98-NM-318-AD. Supersedes AD 98-19-09, Amendment 39-
10751.

    Applicability: All Model 737-100, -200, -300, -400, and -500 
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 (n)(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 detect and correct chafing and prevent electrical arcing 
between the fuel boost pump wiring and the surrounding conduit, 
which could result in arc-through of the conduit, and consequent 
fire or explosion of the fuel tank, accomplish the following:

Inspections Required by AD 98-11-52

    (a) For all airplanes that have accumulated 50,000 or more total 
flight hours as of June 29, 1998 (the effective date of AD 98-11-52, 
amendment 39-10611): Prior to further flight, remove the fuel boost 
pump wiring from the in-tank conduit for the aft boost pumps in main 
tanks numbers 1 and 2, and perform a detailed visual inspection to 
detect damage of the wiring, in accordance with the procedures 
specified in Boeing Alert Service Bulletin 737-28A1120, dated April 
24, 1998, as revised by Notices of Status Change NSC 01, dated May 
7, 1998, NSC 02, dated May 8, 1998, and NSC 03, dated May 9, 1998; 
Boeing Alert Service Bulletin 737-28A1120, Revision 1, dated May 28, 
1998; or Boeing Service Bulletin 737-28A1120, Revision 2, dated 
November 26, 1998.
    (b) For all airplanes that have accumulated less than 50,000 
total flight hours as of receipt of telegraphic AD T98-11-51: Prior 
to the accumulation of 40,000 total flight hours, or within 14 days 
after June 29, 1998, whichever occurs later, remove the fuel boost 
pump wiring from the in-tank conduit for the aft boost pumps in main 
tanks numbers 1 and 2, and perform a detailed visual inspection to 
detect damage of the wiring, in accordance with the procedures 
specified in Boeing Alert Service Bulletin 737-28A1120, dated April 
24, 1998, as revised by Notices of Status Change NSC 01, dated May 
7, 1998, NSC 02, dated May 8, 1998, and NSC 03, dated May 9, 1998; 
Revision 1, dated May 28, 1998; or Revision 2, dated November 26, 
1998.
    (c) For all airplanes: Remove the fuel boost pump wiring from 
the in-tank conduit for the center tank left and right boost pumps, 
and perform a detailed visual inspection to detect damage of the 
wiring, in accordance with the procedures specified in Boeing Alert 
Service Bulletin 737-28A1120, dated April 24, 1998, as revised by 
Notices of Status Change NSC 01, dated May 7, 1998, NSC 02, dated 
May 8, 1998, and NSC 03, dated May 9, 1998; Revision 1, dated May 
28, 1998; or Revision 2, dated November 26, 1998. Accomplish the 
inspection at the earliest of the times specified in paragraphs 
(c)(1), (c)(2), and (c)(3).
    (1) For Model 737-300, -400, and -500 series airplanes: Inspect 
prior to the accumulation of 40,000 total flight hours, or within 14 
days after June 29, 1998, whichever occurs later.
    (2) For Model 737-100 and -200 series airplanes: Inspect prior 
to the accumulation of 40,000 total flight hours, or within 10 days 
after June 29, 1998, whichever occurs later.
    (3) For all airplanes: Inspect prior to the accumulation of 
50,000 total flight hours, or within 5 days after June 29, 1998, 
whichever occurs later.
    (d) For all airplanes: Prior to the accumulation of 30,000 total 
flight hours or within 45 days after June 29, 1998, whichever occurs 
later, remove the fuel boost pump wiring from the in-tank conduit 
for the aft boost pumps in main tanks numbers 1 and 2, and the 
center tank left and right boost pumps, and perform a detailed 
visual inspection to detect damage of the wiring, in accordance with 
the procedures specified in Boeing Alert Service Bulletin 737-
28A1120, dated April 24, 1998, as revised by Notices of Status 
Change NSC 01, dated May 7, 1998, NSC 02, dated May 8, 1998, and NSC 
03, dated May 9, 1998; Revision 1, dated May 28, 1998; or Revision 
2, dated November 26, 1998.

Inspection Required by AD 98-19-09

    (e) For airplanes that have accumulated 20,000 or more total 
flight hours and less than 30,000 total flight hours as of October 
15, 1998 (the effective date of AD 98-19-09, amendment 39-10751): 
Within 60 days after October 15, 1998, remove the fuel boost pump 
wiring from the in-tank conduit for the aft boost pumps in main 
tanks numbers 1 and 2, and the center tank left and right boost 
pumps, and perform a detailed visual inspection to detect damage of 
the wiring; in accordance with the procedures specified in Boeing 
Alert Service Bulletin 737-28A1120, dated April 24, 1998, as revised 
by Notices of Status Change NSC 01, dated May 7, 1998, NSC 02, dated 
May 8, 1998, and NSC 03, dated May 9, 1998; Revision 1, dated May 
28, 1998; or Revision 2, dated November 26, 1998.

New Inspection Requirements

    (f) For airplanes that have accumulated less than 20,000 total 
flight hours as of October

[[Page 1548]]

15, 1998: Remove the fuel boost pump wiring from the in-tank conduit 
for the aft boost pumps in main tanks numbers 1 and 2, and the 
center tank left and right boost pumps, and perform a detailed 
visual inspection to detect damage of the wiring; at the earlier of 
the times specified in paragraphs (f)(1) and (f)(2) of this AD; in 
accordance with the procedures specified in Boeing Alert Service 
Bulletin 737-28A1120, dated April 24, 1998, as revised by Notices of 
Status Change NSC 01, dated May 7, 1998, NSC 02, dated May 8, 1998, 
and NSC 03, dated May 9, 1998; Boeing Alert Service Bulletin 737-
28A1120, Revision 1, dated May 28, 1998; or Boeing Service Bulletin 
737-28A1120, Revision 2, dated November 26, 1998.
    (1) Prior to the accumulation of 20,000 total flight hours, or 
within 60 days after the effective date of this AD, whichever occurs 
later.
    (2) Within 24 months after the effective date of this AD.
    (g) For all airplanes: Repeat the inspection required by 
paragraph (d), (e), or (f) of this AD, as applicable, at intervals 
not to exceed 30,000 flight hours after initial accomplishment of 
the applicable inspection.

Corrective Actions

    (h) If red, yellow, blue, or green wire insulation cannot be 
seen through the outer jacket of the electrical cable during any 
inspection required by this AD: Prior to further flight, accomplish 
paragraph (h)(1), (h)(2), or (h)(3) of this AD in accordance with 
procedures specified in Boeing Alert Service Bulletin 737-28A1120, 
dated April 24, 1998, as revised by Notices of Status Change NSC 01, 
dated May 7, 1998, NSC 02, dated May 8, 1998, and NSC 03, dated May 
9, 1998; Revision 1, dated May 28, 1998; or Revision 2, dated 
November 26, 1998.
    (1) Install Teflon sleeving over the electrical cable, and 
reinstall the cable. Or
    (2) Reinstall the electrical cable without Teflon sleeving over 
the cable. Within 500 flight hours after accomplishment of the 
reinstallation, repeat the inspection described in paragraph (d), 
(e), or (f) of this AD, as applicable, and install Teflon sleeving 
over the cable. Or
    (3) Replace the electrical cable with new cable without Teflon 
sleeving. Within 18 months or 6,000 flight hours, whichever occurs 
first, repeat the inspection specified in paragraph (d), (e), or (f) 
of this AD, as applicable, and install Teflon sleeving over the 
cable.
    (i) If red, yellow, blue, or green wire insulation can be seen 
through the outer jacket of the electrical cable during any 
inspection required by this AD, but no evidence of electrical arcing 
is found: Prior to further flight, accomplish either paragraph 
(i)(1) or (i)(2) of this AD in accordance with the procedures 
specified in Boeing Alert Service Bulletin 737-28A1120, dated April 
24, 1998, as revised by Notices of Status Change NSC 01, dated May 
7, 1998, NSC 02, dated May 8, 1998, and NSC 03, dated May 9, 1998; 
Boeing Alert Service Bulletin 737-28A1120, Revision 1, dated May 28, 
1998; or Boeing Service Bulletin 737-28A1120, Revision 2, dated 
November 26, 1998.
    (1) Replace the damaged electrical cable with a new cable, 
install Teflon sleeving over the cable, and reinstall the cable. Or
    (2) Replace the electrical cable with a new cable without Teflon 
sleeving. Within 18 months or 6,000 flight hours, whichever occurs 
first, repeat the inspection described in paragraph (d), (e), or (f) 
of this AD, as applicable, and install Teflon sleeving over the 
cable.
    (j) If any evidence of electrical arcing but no evidence of fuel 
leakage is found on the removed electrical cable during any 
inspection required by this AD: Prior to further flight, accomplish 
paragraphs (j)(1) and (j)(2) of this AD in accordance with the 
procedures specified in Boeing Alert Service Bulletin 737-28A1120, 
dated April 24, 1998, as revised by Notices of Status Change NSC 01, 
dated May 7, 1998, NSC 02, dated May 8, 1998, and NSC 03, dated May 
9, 1998; Boeing Alert Service Bulletin 737-28A1120, Revision 1, 
dated May 28, 1998; or Boeing Service Bulletin 737-28A1120, Revision 
2, dated November 26, 1998.
    (1) Verify the integrity of the conduit in accordance with the 
instructions contained in NSC 03, Revision 1, or Revision 2 of the 
alert service bulletin. And
    (2) Accomplish either paragraph (j)(2)(i) or (j)(2)(ii) of this 
AD in accordance with the alert service bulletin.
    (i) Replace the damaged electrical cable with a new cable, 
install Teflon sleeving over the cable, and reinstall the cable. Or
    (ii) Replace the electrical cable with a new cable without 
Teflon sleeving. Within 18 months or 6,000 flight hours, whichever 
occurs first, repeat the inspection described in paragraph (d), (e), 
or (f) of this AD, as applicable, and install Teflon sleeving over 
the cable.
    (k) If any evidence of fuel is found on the removed electrical 
cable during any inspection required by this AD: Prior to further 
flight, accomplish paragraphs (k)(1) and (k)(2) of this AD in 
accordance with the procedures specified in Boeing Alert Service 
Bulletin 737-28A1120, dated April 24, 1998, as revised by Notices of 
Status Change NSC 01, dated May 7, 1998, NSC 02, dated May 8, 1998, 
and NSC 03, dated May 9, 1998; Boeing Alert Service Bulletin 737-
28A1120, Revision 1, dated May 28, 1998; or Boeing Service Bulletin 
737-28A1120, Revision 2, dated November 26, 1998.
    (1) Replace the conduit section where electrical arcing was 
found. And
    (2) Accomplish either paragraph (k)(2)(i) or (k)(2)(ii) of this 
AD.
    (i) Replace the damaged electrical cable with a new cable, 
install Teflon sleeving over the cable, and reinstall the cable. Or
    (ii) Replace the electrical cable with a new cable without 
Teflon sleeving. Within 18 months or 6,000 flight hours, whichever 
occurs first, repeat the inspection described in paragraph (d), (e), 
or (f) of this AD, as applicable, and install Teflon sleeving over 
the cable.
    (l) For Groups 1 and 2 airplanes, as identified in Boeing Alert 
Service Bulletin 737-28A1120, dated April 24, 1998: Concurrent with 
the first accomplishment of corrective action in accordance with 
paragraph (h), (i), (j), or (k) of this AD, as applicable, replace 
the case ground wire with a new wire in accordance with Boeing Alert 
Service Bulletin 737-28A1120, dated April 24, 1998, as revised by 
Notices of Status Change NSC 01, dated May 7, 1998, NSC 02, dated 
May 8, 1998, and NSC 03, dated May 9, 1998; Boeing Alert Service 
Bulletin 737-28A1120, Revision 1, dated May 28, 1998; or Boeing 
Service Bulletin 737-28A1120, Revision 2, dated November 26, 1998.
    (m) If any damage specified in paragraph (h), (i), or (j) of 
this AD is found during the initial inspection required by paragraph 
(a), (b), (c), (d), (e), or (f) of this AD, as applicable: Within 10 
days after accomplishing that initial inspection, accomplish 
paragraphs (m)(1) and (m)(2) of this AD. 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.
    (1) Submit any damaged electrical cables and conduits to Boeing, 
in accordance with Boeing Alert Service Bulletin 737-28A1120, dated 
April 24, 1998, as revised by Notices of Status Change NSC 01, dated 
May 7, 1998, NSC 02, dated May 8, 1998, and NSC 03, dated May 9, 
1998; Boeing Alert Service Bulletin 737-28A1120, Revision 1, dated 
May 28, 1998; or Boeing Service Bulletin 737-28A1120, Revision 2, 
dated November 26, 1998. Include the serial number of the airplane, 
the number of total flight hours and flight cycles accumulated on 
the airplane, and the location of the electrical cable on the 
airplane.
    (2) For airplanes that are inspected after June 29, 1998, submit 
the serial number of the airplane, the number of total flight hours 
and flight cycles accumulated on the airplane, and the location of 
the electrical cable on the airplane to the Manager, Seattle 
Aircraft Certification Office (ACO), FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; 
fax (425) 227-1181.
    (n)(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 Aircraft Certification 
Office (ACO), FAA, Transport Airplane Directorate. Operators shall 
submit their requests through an appropriate FAA Principal 
Maintenance Inspector, who may add comments and then send it to the 
Manager, Seattle ACO.
    (n)(2) Alternative methods of compliance, approved previously in 
accordance with AD 98-11-52 and AD 98-19-09, are approved as 
alternative methods of compliance with this AD.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Seattle ACO.

    (o) 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.


[[Page 1549]]


    Issued in Renton, Washington, on December 31, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-482 Filed 1-8-99; 8:45 am]
BILLING CODE 4910-13-U