[Federal Register Volume 61, Number 35 (Wednesday, February 21, 1996)]
[Rules and Regulations]
[Pages 6500-6501]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-2869]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-NM-53-AD; Amendment 39-9511; AD 96-03-14]


Airworthiness Directives; Boeing Model 747-400 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain Boeing Model 747-400 series airplanes, that 
currently requires replacement of electrical wiring to the fuel shutoff 
valve for each engine. This amendment requires replacement of the fuel 
shutoff valve wire and sleeve with a wire in two non-metallic sleeves 
in the conduit in the struts of each engine. This amendment is prompted 
by reports of additional occurrences of chafing and shorting of the 
wiring of the engine fuel shutoff valves. The actions specified by this 
AD are intended to prevent such chafing and shorting, which could 
result in the pilot's inability to shut off the supply of fuel in the 
event of an engine fire.

DATES: Effective March 22, 1996.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of March 22, 1996.

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: Stephen Oshiro, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130S, FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; 
telephone (206) 227-2793; fax (206) 227-1181.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 89-14-04, 
amendment 39-6246 (54 FR 27157, June 28, 1989), which is applicable to 
certain Boeing Model 747-400 series airplanes, was published in the 
Federal Register on September 7, 1995 (60 FR 46542). The action 
proposed to supersede AD 89-14-04 to require replacement of the wire 
and sleeve with a single wire in two non-metallic sleeves in the 
conduit in the struts of each engine.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.
    One commenter supports the proposed rule.
    Several commenters request that the compliance time for 
accomplishment of the replacement be extended from the proposed 12 
months. Two of these commenters request an extension that will allow 
the replacement to be accomplished during a regularly scheduled ``C'' 
check (15 to 18 months), when the airplanes will be brought to a main 
base for an extended hold. These two commenters state that, in order to 
accomplish the replacement with the proposed compliance time, they 
would have to special schedule their fleet of airplanes, which would 
entail considerable additional expense. Another commenter states that 
it is currently accomplishing the modification required by AD 95-13-05, 
amendment 39-9285 (60 FR 33333, June 28, 1995), which includes a wiring 
modification that is equivalent to that proposed in the notice. This 
commenter further states that it will complete that modification in 
approximately four years; therefore, compliance with the proposed 
wiring replacement should be extended accordingly.
    The FAA does not concur. In developing an appropriate time for this 
action, the FAA considered not only the degree of urgency associated 
with addressing the subject unsafe condition, but the availability of 
required parts and the practical aspects of accomplishing the required 
replacement during affected operators' scheduled maintenance visits. In 
addition, the FAA has received reports that the wire chafing condition 
led to short circuits on airplanes that had accumulated 12,000 to 
18,310 total flight hours after the incorporation of the modification 
required by AD 89-14-04. In light of this, the FAA has determined that 
the accumulated flight hours of some of the affected airplanes may be 
close to this range at the end of the 12 month compliance time. The FAA 
has also determined that a compliance time of 4 years for incorporation 
of the modification, as required by AD 95-13-05, is unacceptable. Such 
a compliance time would not address the subject unsafe condition in a 
timely manner. However, under the provisions of paragraph (b) of the 
final rule, the FAA may approve request for adjustments to the 
compliance time if data are presented to justify such an adjustment.
    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 as proposed.
    There are approximately 311 Model 747-400 series airplanes of the 
affected design in the worldwide fleet. The FAA estimates that 38 
airplanes of U.S. registry will be affected by this AD, that it will 
take approximately 80 work hours per airplane to accomplish the 
required action, at that the average labor rate of $60 per work hour. 
Required parts will cost approximately $673 per airplane. Based on 
these figures, the cost impact on U.S. operators of the new 
requirements of this AD is estimated to be $207,974, or $5,473 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.
    The regulations adopted herein will 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 final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    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 

[[Page 6501]]
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.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-6246 (54 FR 
27157, June 28, 1989), and by adding a new airworthiness directive 
(AD), amendment 39-9511, to read as follows:

96-03-14 Boeing: Amendment 39-9511. Docket 95-NM-53-AD. Supersedes 
AD 89-14-04, Amendment 39-6246.

    Applicability: Model 747-400 series airplanes; line positions 
696 through 1046 inclusive, except airplane variable numbers RT502 
and RU032 (airplane serial numbers 24062 and 25780, respectively); 
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 the inability to shut off the supply of fuel in the 
event of an engine fire, accomplish the following:
    (a) Within 12 months after the effective date of this AD, 
replace the fuel shutoff valve wire and sleeve with a wire in two 
non-metallic sleeves in the conduit in the struts of each engine, in 
accordance with Boeing Alert Service Bulletin 747-28A2186, dated 
January 19, 1995.

    Note 2: Replacements accomplished prior to the effective date of 
this amendment in accordance with Boeing Alert Service Bulletin 747-
54A2157, dated January 12, 1995, or Revision 1, dated August 3, 
1995; or Boeing Alert Service Bulletin 747-54A2156, dated December 
15, 1994, or Revision 1, dated July 20, 1995; are considered 
acceptable for compliance with the replacements specified in this 
amendment.

    (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 3: 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.
    (d) The replacement shall be done in accordance with Boeing 
Alert Service Bulletin 747-28A2186, dated January 19, 1995. 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.
    (e) This amendment becomes effective on March 22, 1996.

    Issued in Renton, Washington, on February 5, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-2869 Filed 2-20-96; 8:45 am]
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