AD 2000-16-14

[Federal Register Volume 65, Number 162 (Monday, August 21, 2000)]
[Rules and Regulations]
[Pages 50630-50632]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-20963]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-54-AD; Amendment 39-11871; AD 2000-16-14]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 767-200, -300, and -300F 
Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Boeing Model 767-200, -300, and -300F series 
airplanes. This AD requires 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 amendment 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 this 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: Effective September 25, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 25, 2000.

ADDRESSES: The service information referenced in this AD may be 
obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, 
Washington 98124-2207. This information may be examined at the Federal 
Aviation Administration (FAA), Transport Airplane Directorate, Rules 
Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of 
the Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.

FOR FURTHER INFORMATION CONTACT: Elias Natsiopoulos, Aerospace 
Engineer, Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055-
4056; telephone (425) 227-1279; fax (425) 227-1181.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD)

[[Page 50631]]

that is applicable to certain Boeing Model 767-200, -300, and -300F 
series airplanes was published in the Federal Register on February 2, 
2000 (65 FR 4904). That action proposed to 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.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Support for the Proposal

    One commenter concurs with the proposed rule.

Request To Revise Secondary Reference

    One commenter points out that ``NOTE 2'' of the proposed rule 
reads, ``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.'' The 
commenter notes that the original issue of Grimes Service Bulletin 60-
3414-33-SB01 has been revised by issuance of Revision 1, dated February 
17, 2000. The commenter requests that the FAA revise the proposed AD to 
reference Revision 1 of that service bulletin. The FAA concurs with the 
commenter's request, although the FAA notes that the correct date for 
Revision 1 of the Grimes service bulletin is March 13, 2000. The FAA 
has revised ``NOTE 2'' of this AD accordingly.

Request To Extend Compliance Time, Add Repetitive Inspections

    One commenter requests that the compliance time for the 
modification or replacement of the cable assembly be extended from 
1,800 flight hours to 16,000 flight hours or 3 years. The commenter 
concurs with the proposal to require the initial inspection and repair, 
if necessary, at 1,800 flight hours, and recommends repetitive 
inspections at intervals not to exceed 1,800 flight hours until 
accomplishment of the modification or replacement of the cable 
assembly. The commenter states that the proposed compliance time of 
1,800 flight hours after the effective date of this AD does not provide 
ample time for the modification or replacement to be accomplished 
during a major maintenance visit. The commenter states that not 
accomplishing the modification or replacement at a regularly scheduled 
major maintenance visit will increase the cost of the proposed AD to 
operators. The commenter also asserts that its recommendation will 
ensure that the airplanes will continue to operate safely.
    The FAA does not concur with the commenter's request. As noted in 
the proposed rule, the subject cable assembly is located under the 
center fuel tank--a flammable leakage zone. Modification or replacement 
of the cable assembly as required by this AD is necessary to prevent 
wire chafing, which could result in electrical arcing or sparking in 
this flammable leakage zone. Considering the critical nature of this 
unsafe condition, the FAA finds that 1,800 flight hours is an 
appropriate compliance time in which the affected airplanes can 
continue to operate before accomplishment of the requirements of this 
AD. The FAA notes that the compliance time of 1,800 flight hours is 
adequate for most affected operators to schedule accomplishment of this 
AD at the next maintenance visit after the effective date of this AD. 
No change to the final rule is necessary in this regard.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes previously 
described. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    There are approximately 740 Model 767-200, -300, and -300F series 
airplanes of the affected design in the worldwide fleet. The FAA 
estimates that 263 airplanes of U.S. registry will be affected by this 
AD.
    In lieu of accomplishing the replacement, it will 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 
inspection and modification according to this AD, at an average labor 
rate of $60 per work hour. Required parts will cost approximately $157 
per airplane. Based on these figures, the cost impact of the inspection 
and modification that is one means of compliance with this AD is 
estimated to be $337 per airplane.
    In lieu of accomplishing the inspection and modification, it will 
take approximately 3 work hours per airplane to accomplish the 
replacement according to this AD, at an average labor rate of $60 per 
work hour. Required parts will 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 the replacement that is one means of 
compliance with this AD 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 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 adopted herein will not have a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends 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.

[[Page 50632]]

Sec. 39.13  [Amended]


    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

2000-16-14  Boeing: Amendment 39-11871. 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, 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 required by 
paragraph (a)(1) of this AD. Since the issuance of the Boeing 
service bulletin, Grimes has issued Service Bulletin 60-3414-33-
SB01, Revision 1, dated March 13, 2000. Revision 1 of the Grimes 
service bulletin is 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. 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 
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.

Incorporation by Reference

    (d) The actions shall be done in accordance with Boeing Service 
Bulletin 767-33A0075, Revision 1, dated May 27, 1999. This 
incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be obtained from Boeing Commercial Airplane Group, 
P.O. Box 3707, Seattle, Washington 98124-2207. Copies may be 
inspected at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

Effective Date

    (e) This amendment becomes effective on September 25, 2000.

    Issued in Renton, Washington, on August 11, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-20963 Filed 8-18-00; 8:45 am]
BILLING CODE 4910-13-U