[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]



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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