[Federal Register Volume 65, Number 22 (Wednesday, February 2, 2000)]
[Proposed Rules]
[Pages 4904-4906]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-2225]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-54-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 767-200, -300, and -300F 
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 767-200, -
300, and -300F series airplanes. This proposal would require either an 
inspection to detect damage or chafing of the insulation or wires, 
modification of the cable assembly, and repairs, if necessary; or 
replacement of the cable assembly of the lower anti-collision light 
with a new cable assembly. This proposal is prompted by reports of 
electrical arcing on structure near the lower body anti-collision light 
due to chafing of the cable. The actions specified by the proposed AD 
are intended to prevent such chafing as a result of improper 
installation of the lower body anti-collision light assembly, which 
could result in electrical arcing or sparking in a flammable leakage 
zone of the airplane.

  DATES: Comments must be received by March 20, 2000.

ADDRESSES:  Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 99-NM-54-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 Flight Test Branch, ANM-130S, FAA, Transport 
Airplane Directorate, Seattle Aircraft Certification Office, 1601 Lind 
Avenue, S.W., 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 99-NM-54-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-54-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The FAA has received reports of evidence of electrical arcing on 
structure near the lower body anti-collision light on Boeing Model 767-
200 and -300 series airplanes. The lower body anti-collision light is 
installed below the center fuel tank in a flammable leakage zone. 
Results of an operator survey and a review of installation drawings 
revealed that it is possible to install the lower body anti-collision 
light assembly backwards with the aft edge forward. This incorrect 
orientation of the light assembly results in misalignment of the 
connector and cable with the opening of the web, which necessitates a 
sharp bend of the cable for routing through the web opening. A sharply 
bent cable loop against the structure causes chafing and eventual wire 
damage of the cable. This condition, if not corrected, could result in 
electrical arcing or sparking in a flammable leakage zone of the 
airplane.
    The subject cable assembly of the lower anti-collision light on 
Boeing Model 767-300F series airplanes is identical to that of the 
affected Boeing Model 767-200 and -300 series airplanes. Therefore, all 
of these airplanes may be subject to the same unsafe condition.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Service Bulletin 767-
33A0075, Revision 1, dated May 27, 1999. The service bulletin describes 
procedures for repetitive general visual inspections to detect damage 
or chafing of the insulation or wires of the lower body anti-collision 
light, and repair, if necessary. In lieu of accomplishing the 
repetitive inspections, the service bulletin also describes procedures 
for either modification of the cable assembly, and repairs, if 
necessary; or replacement of the cable assembly of the lower anti-
collision light with a new cable assembly. The modification involves 
removing the strain relief and bushing, installing a backshell extender 
with a new strain relief, and re-identifying the part number of the 
cable assembly.
    Boeing Service Bulletin 767-33A0075, Revision 1, dated May 27, 
1999, refers to Grimes Service Bulletin 60-3414-33-SB01, dated December 
8, 1998, as an additional source of service information for 
accomplishment of the modification described previously.

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 service bulletin described previously, except as discussed below.

Differences Between Proposed Rule and Service Bulletin

    The proposed AD would differ from the service bulletin in that it 
would mandate, within 1,800 flight hours after the effective date of 
this AD, either a one-time general visual inspection to detect damage 
or chafing of the insulation or wires, modification of the cable 
assembly of the lower body anti-collision cable assembly, and repairs, 
if necessary; or replacement of the cable

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assembly of the lower anti-collision light with a new cable assembly. 
The service bulletin provides for the modification or replacement as 
optional.
    The FAA has determined that long-term continued operational safety 
will be better assured by design changes to remove the source of the 
problem, rather than by repetitive inspections. Long-term inspections 
may not be providing the degree of safety assurance necessary for the 
transport airplane fleet. This, coupled with a better understanding of 
the human factors associated with numerous continual inspections, has 
led the FAA to consider placing less emphasis on inspections and more 
emphasis on design improvements. The proposed modification or 
replacement requirement is in consonance with these conditions.

Cost Impact

    There are approximately 740 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 263 airplanes of U.S. registry 
would be affected by this proposed AD.
    In lieu of accomplishing the replacement, it would take 
approximately 3 work hours (1 work hour per airplane for the inspection 
and 2 work hours per airplane for the modification) to accomplish the 
proposed inspection and modification. Required parts would cost 
approximately $157 per airplane. Based on these figures, the cost 
impact of the inspection and modification proposed by this AD on U.S. 
operators is estimated to be $337 per airplane.
    In lieu of accomplishing the inspection and modification, it would 
take approximately 3 work hours per airplane to accomplish the proposed 
replacement, at an average labor rate of $60 per work hour. Required 
parts would cost approximately $1,552 (for Group 1 airplanes) or $2,234 
(for Group 2 airplanes) per airplane. Based on these figures, the cost 
impact of this replacement proposed by this AD on U.S. operators is 
estimated to be $1,732 (for Group 1 airplanes) or $2,414 (for Group 2 
airplanes) per airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the 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 adding the following new 
airworthiness directive:

Boeing: Docket 99-NM-54-AD.

    Applicability: Model 767-200, -300, -300F series airplanes, line 
numbers 1 through 739 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 (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 chafing as a result of improper installation of the 
cable assembly of the lower body anti-collision light, which could 
result in electrical arcing or sparking in a flammable leakage zone of 
the airplane, accomplish the following:

Modification or Replacement

    (a) Within 1,800 flight hours after the effective date of this AD, 
perform the actions in either paragraph (a)(1) or (a)(2) of this AD in 
accordance with Boeing Service Bulletin 767-33A0075, Revision 1, dated 
May 27, 1999.
    (1) Perform a one-time general visual inspection to detect damage 
or chafing of the insulation or wires, and modify the cable assembly of 
the lower body anti-collision cable assembly. If any damage or chafing 
is detected, prior to further flight, repair the damaged or chafed 
part.

    Note 2:
     Boeing Service Bulletin 767-33A0075, Revision 1, May 27, 1999, 
refers to Grimes Service Bulletin 60-3414-33-SB01, dated December 8, 
1998, as an additional source of service information for accomplishment 
of the modification required by paragraph (a)(1) of this AD.


    Note 3:
     For the purposes of this AD, a general visual inspection is 
defined as ``A visual examination of an interior or exterior area, 
installation, or assembly to detect obvious damage, failure, or 
irregularity. This level of inspection is made under normally available 
lighting conditions such as daylight, hangar lighting, flashlight, or 
drop-light, and may require removal or opening of access panels or 
doors. Stands, ladders, or platforms may be required to gain proximity 
to the area being checked.''

    (2) Replace the cable assembly of the lower body anti-collision 
cable assembly with a new cable assembly.

Alternative Methods of Compliance

    (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 4:
     Information concerning the existence of approved alternative 
methods of compliance with this AD, if any, may be obtained from the 
Seattle ACO.

Special Flight Permits

    (c) Special flight permits may be issued in accordance with 
Secs. 21.197 and

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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 January 27, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-2225 Filed 2-1-00; 8:45 am]
BILLING CODE 4910-13-U