[Federal Register Volume 64, Number 31 (Wednesday, February 17, 1999)]
[Proposed Rules]
[Pages 7829-7830]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-3734]
[[Page 7829]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-193-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 767 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to certain Boeing Model 767 series
airplanes. This proposal would require a one-time inspection to detect
discrepancies of the wire expando sleeve of the wire bundles adjacent
to the landing gear control lever module; certain follow-on actions and
repair, if necessary; and wrapping the wire expando sleeve with tape or
zippertubing and tape. This proposal is prompted by reports indicating
that the landing gear failed to extend on an in-service airplane, and
that the cable of the landing gear control lever was severed on a
second in-service airplane. The actions specified by the proposed AD
are intended to prevent interference and consequent arcing between the
landing gear control lever and the wire bundles adjacent to the landing
gear control lever module, which could result in inability to extend
the landing gear prior to landing.
DATES: Comments must be received by April 5, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-193-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.
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: Elias Natsiopoulos, Aerospace
Engineer, Systems and Equipment Branch, ANM-130S, FAA, Transport
Airplane Directorate, Seattle Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-1279;
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-193-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-193-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The FAA has received a report indicating that, prior to landing an
in-service Boeing Model 767 series airplane, the flightcrew was unable
to extend the landing gear because the landing gear control lever
failed to move from the ``UP'' to ``OFF'' position. Consequently, the
flightcrew was forced to extend the landing gear by depressurizing the
center hydraulic system.
In addition, the FAA has received a report indicating that,
following take-off of a second Boeing Model 767 series airplane, the
flightcrew was unable to retract the landing gear. The flightcrew was
forced to return the airplane to its original departure airport.
Investigation revealed that the landing gear control lever interfered
with the wire expando sleeve, which contains the wire bundles of the
alternate extension system of the landing gear. This interference
caused the wires of the alternate extension system of the landing gear
to arc. Repeated arcing over a period of time severed the cable of the
landing gear control lever. This condition, if not corrected, could
result in inability to extend the landing gear prior to landing.
Explanation of Relevant Service Information
The FAA has reviewed and approved Boeing Alert Service Bulletin
767-32A0163, dated March 5, 1998, and Boeing Service Bulletin 767-
32A0163, Revision 1, dated October 1, 1998. The alert service bulletin
and Revision 1 describe procedures for a one-time visual inspection to
detect discrepancies (i.e., cuts, abrasions, fraying, and arcing) of
the wire expando sleeve of the wire bundles adjacent to the landing
gear control lever module; certain follow-on actions (i.e., visual
inspection of the varglas layer and wire bundles adjacent to the
landing gear control lever module), if necessary; and repair, if
necessary. The alert service bulletin and Revision 1 also describe
procedures for wrapping the wire expando sleeve with tape or
zippertubing and tape. Accomplishment of the actions specified in the
alert service bulletin or Revision 1 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 require accomplishment of the actions specified in
the alert service bulletin or Revision 1 described previously.
Cost Impact
There are approximately 666 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 268 airplanes of U.S. registry
would be affected by this proposed AD.
It would take approximately 1 work hour per airplane to accomplish
the proposed actions, at an average labor rate of $60 per work hour.
The cost of required parts would be nominal. Based on these figures,
the cost impact of the proposed AD on U.S. operators is estimated to be
$16,080, or $60 per airplane.
The cost impact figure discussed above is based on assumptions that
no operator has yet accomplished any of the proposed requirements of
this AD
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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 adding the following new
airworthiness directive:
Boeing: Docket 98-NM-193-AD.
Applicability: Model 767 series airplanes, as listed in Boeing
Alert Service Bulletin 767-32A0163, Revision 1, October 1, 1998;
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 (b) 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 interference and consequent arcing between the
movement of the landing gear control lever and the wire bundles
adjacent to the landing gear control lever module, which could
result in inability to extend the landing gear prior to landing,
accomplish the following:
(a) Within 90 days after the effective date of this AD, perform
a one-time visual inspection to detect discrepancies (i.e., cut,
abrasion, fraying, and arcing) of the wire expando sleeve of the
wire bundles adjacent to the landing gear control lever module, in
accordance with Boeing Alert Service Bulletin 767-32A0163, dated
March 5, 1998, or Revision 1, dated October 1, 1998.
(1) If no discrepancy of the wire expando sleeve is detected,
prior to further flight, wrap the wire expando sleeve with tape or
zippertubing and tape, in accordance with the alert service bulletin
or Revision 1.
(2) If any discrepancy of the wire expando sleeve is detected,
prior to further flight, perform a visual inspection to detect
discrepancies of the varglas layer, in accordance with the alert
service bulletin or Revision 1.
(i) If no discrepancy of the varglas layer is detected, prior to
further flight, repair the wire expando sleeve and wrap it with tape
or zippertubing and tape, in accordance with the alert service
bulletin or Revision 1.
(ii) If any discrepancy of the varglas layer is detected, prior
to further flight, perform a visual inspection to detect
discrepancies of the wire bundles, in accordance with the alert
service bulletin or Revision 1.
(A) If no discrepancy of the wire bundles is detected, prior to
further flight, rewrap the wires with new varglas layer, repair the
wire expando sleeve, and wrap the wire expando sleeve with tape or
zippertubing and tape, in accordance with the alert service bulletin
or Revision 1.
(B) If any discrepancy of the wire bundles is detected, prior to
further flight, repair the wires, rewrap the wire bundles with new
varglas layer, repair wire expando sleeve, and wrap the wire expando
sleeve with tape or zippertubing and tape, in accordance with the
alert service bulletin or Revision 1.
(b) 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.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Seattle ACO.
(c) 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 February 9, 1999.
John J. Hickey,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-3734 Filed 2-16-99; 8:45 am]
BILLING CODE 4910-13-U
