[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
