[Federal Register Volume 64, Number 120 (Wednesday, June 23, 1999)]
[Rules and Regulations]
[Pages 33394-33397]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-15775]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-121-AD; Amendment 39-11199; AD 99-12-52]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 727 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This document publishes in the Federal Register an amendment 
adopting Airworthiness Directive (AD) T99-12-52 that was sent 
previously to all known U.S. owners and operators of all Boeing Model 
727 series airplanes by individual telegrams. This AD requires a boost 
pump dry bay inspection to detect leakage of fuel through an arced-
through conduit, and corrective action, as necessary. This AD also 
requires repetitive detailed visual inspections of the in-tank fuel 
boost pump wiring to detect chafing of the wire insulation, evidence of 
electrical arcing, or arc-through of the conduit wall on Model 727 
series airplanes, and applicable corrective action; and installation of 
sleeving over the in-tank fuel boost pump wires as a method to protect 
the wiring from chafing. This action is prompted by reports of severe 
wear of in-tank fuel boost pump wiring, and arc-through of the 
surrounding conduit on two Model 727 series airplanes. The actions 
specified by this AD are intended to prevent fuel tank explosion 
resulting from arc-through of the fuel boost pump wiring conduits.

DATES: Effective June 28, 1999, to all persons except those persons to 
whom

[[Page 33395]]

it was made immediately effective by telegraphic AD T99-12-52, issued 
May 24, 1999, which contained the requirements of this amendment.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 28, 1999.
    Comments for inclusion in the Rules Docket must be received on or 
before August 23, 1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 99-NM-121-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056.
    The applicable service information 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; or at the 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Jon Regimbal, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Transport Airplane Directorate, 
Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056; telephone (425) 227-2687; fax (425) 227-1181.

SUPPLEMENTARY INFORMATION:

Issuance of Telegraphic AD T99-12-51

    On May 21, 1999, the FAA issued telegraphic AD T99-12-51, which is 
applicable to all Boeing Model 727 series airplanes, to require a boost 
pump dry bay inspection to detect leakage of fuel through an arced-
through conduit, and corrective action, as necessary.
    Telegraphic AD T99-12-51 was prompted by reports of severe wear of 
the in-tank fuel boost pump wiring, and arc-through of the surrounding 
conduit on two Model 727 series airplanes that had accumulated in 
excess of 50,000 total flight hours. The wear and arc-through condition 
of the conduit surrounding the in-tank fuel boost pump wiring has been 
attributed to chafing between the in-tank fuel boost pump wiring and 
the wall of the surrounding conduit, exposing the electrical conductor 
of the boost pump power wire and placing it in contact with the 
aluminum wall of the conduit, resulting in arc-through of the conduit 
wall. Arc-through of the conduit presents an ignition source inside the 
fuel tank. In addition, the resultant hole in the conduit provides a 
path for fuel to leak from the fuel tank. The actions required by 
telegraphic AD T99-12-51 were intended to detect and correct fuel boost 
pump wiring conduits which have experienced severe chafing and 
electrical arcing, resulting in burn-through of the conduit. This 
condition, if not corrected, could result in ignition of fuel vapors in 
a fuel tank, and a fuel tank explosion.

Issuance of Telegraphic AD T99-12-52

    On May 24, 1999, the FAA issued telegraphic AD T99-12-52, 
applicable to all Model 727 series airplanes, which superseded 
telegraphic AD T99-12-51 to continue to require a boost pump dry bay 
inspection to detect leakage of fuel through an arced-through conduit, 
and corrective action, as necessary.
    Telegraphic AD T99-12-52 adds a requirement for repetitive detailed 
visual inspections of the in-tank fuel boost pump wiring to detect 
chafing of the wire insulation, evidence of electrical arcing, or arc-
through of the conduit wall on Model 727 series airplanes, and 
applicable corrective action. In addition, this telegraphic AD requires 
installation of sleeving over the in-tank fuel boost pump wires as a 
method to protect the wiring from chafing. If the initial inspection of 
the wiring is performed before the inspection of the fuel boost pump 
dry bay for fuel leaks, the inspection of the fuel boost pump dry bay 
for fuel leaks is not required.
    Telegraphic AD T99-12-52 was prompted by the same reports that are 
described in the Summary of this AD and in telegraphic AD T99-12-51.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Alert Service Bulletin 
727-28A0126, dated May 24, 1999, which describes procedures for 
performing a boost pump dry bay inspection to detect leakage of fuel 
through an arced-through conduit. That alert service bulletin also 
describes procedures for performing detailed inspections of the in-tank 
fuel boost pump wire bundles, installing wire bundle sleeving, 
replacing the conduit if fuel leakage is detected, and performing 
applicable corrective actions. In addition, the alert service bulletin 
describes procedures for performing leak checks of the replaced conduit 
and installing the new fuel boost pump wire.

Explanation of Requirements of the Rule

    Since the unsafe condition described is likely to exist or develop 
on other airplanes of the same type design, the FAA issued telegraphic 
AD T99-12-52 to prevent fuel tank explosion resulting from arc-through 
of the fuel boost pump wiring conduits. This AD supersedes telegraphic 
AD T99-12-51 to continue to require a boost pump dry bay inspection to 
detect leakage of fuel through an arced-through conduit, and corrective 
action, as necessary. This AD adds a requirement for repetitive 
detailed visual inspections of the in-tank fuel boost pump wiring to 
detect chafing of the wire insulation, evidence of electrical arcing, 
or arc-through of the conduit wall on Model 727 series airplanes, and 
applicable corrective action. In addition, this AD requires 
installation of sleeving over the in-tank fuel boost pump wires as a 
method to protect the wiring from chafing. If the initial inspection of 
the wiring is performed before the inspection of the boost pump dry bay 
for fuel leaks, the inspection of the fuel boost pump dry bay for fuel 
leaks is not required.
    Except as described in the ``Differences'' paragraph below, the 
actions are required to be accomplished in accordance with Boeing All 
Operator Message (AOM) M-7200-99-04035, dated May 21, 1999, (for the 
boost pump dry bay inspection), and Boeing Alert Service Bulletin 727-
28A0126, dated May 24, 1999, (for the boost pump dry bay inspection and 
the wiring inspection).

Differences Between This AD and the Service Information

    Although the Boeing AOM describes general procedures for inspecting 
the fuel boost pump wire bundles and installing new fuel boost pump 
wire bundles and sleeving, the FAA considers that use of the more 
specific instructions included in Boeing Alert Service Bulletin 727-
28A0126, dated May 24, 1999, is necessary to ensure that the wire 
inspections are performed properly.
    However, if the wire bundle inspection or wire bundle replacement 
has been accomplished in accordance with the Boeing AOM, these actions 
may provide the basis for an alternative method of compliance as 
provided in paragraph (l) of this AD.
    Since it was found that immediate corrective action was required, 
notice and opportunity for prior public comment thereon were 
impracticable and contrary to the public interest, and good cause 
existed to make the AD effective immediately by individual telegrams 
issued on May 24, 1999, to all known U.S. owners and operators of all 
Model 727 series airplanes. These conditions still exist, and the AD is 
hereby published in the Federal

[[Page 33396]]

Register as an amendment to section 39.13 of the Federal Aviation 
Regulations (14 CFR 39.13) to make it effective to all persons.

Explanation of Changes Made to the Final Rule

    The FAA has determined that reference to a certain paragraph that 
was included in the ``Differences'' paragraph and in NOTE 1 of 
Telegraph AD T99-12-52 is incorrect. The FAA has revised this AD to 
correctly reference paragraph (l) instead of paragraph (e).

Interim Action

    In the preamble to AD T99-12-51, the FAA indicated that the actions 
required by that AD were considered ``interim action'' and that further 
rulemaking action was being considered. The FAA now has determined that 
further rulemaking action is indeed necessary, and this AD follows from 
that determination.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this 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 under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the 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 that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 99-NM-121-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    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.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, 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.


Sec. 39.13  [Amended]

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

99-12-52  Boeing: Amendment 39-11199. Docket 99-NM-121-AD. 
Supersedes Telegraphic AD T99-12-51.

    Applicability: All Model 727 series airplanes, 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 (l) 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 fuel tank explosion resulting from arc-through of the 
fuel boost pump wiring conduits, accomplish the following:
    (a) For airplanes with 50,000 or more total flight hours as of 
the date of receipt of AD T99-12-51, within 5 days after the 
effective date of this AD, accomplish the requirements of paragraph 
(c) of this AD.
    (b) For airplanes with less than 50,000 total flight hours as of 
the date of receipt of AD T99-12-51, prior to the accumulation of 
30,000 total flight hours, or within 10 days after receipt of this 
AD, whichever occurs later, accomplish the requirements of paragraph 
(c) of this AD.

Initial Inspection and Corrective Action

    (c) Except as provided in paragraphs (d) and (e) of this AD, 
perform a boost pump dry bay inspection and applicable follow-on 
corrective actions, in accordance with steps 1 through 6 of the 
``Boost Pump Dry Bay Inspection,'' specified in Boeing All Operator 
Message M-7200-99-04035, dated May 21, 1999, or in accordance with 
Boeing Alert Service Bulletin 727-28A0126, dated May 24, 1999.
    (d) For airplanes on which the actions specified in step 5-E-<3> 
of Boeing All Operator Message M-7200-99-04035, dated May 21, 1999, 
are accomplished, the fuel tank in which the conduit has been 
replaced must be refueled prior to accomplishing step 6.
    (e) Accomplishment of the requirements of paragraph (c) of this 
AD is not required if the requirements of paragraph (i) of this AD 
are accomplished within the times specified in paragraph (a) or (b) 
of this AD, as applicable.

New Requirements of This AD

    (f) For airplanes with 50,000 or more total flight hours as of 
the effective date of this AD, within 20 days after the effective 
date of this AD, accomplish the requirements of paragraph (i) of 
this AD.
    (g) For airplanes with less than 50,000 total flight hours, but 
more than 30,000 total flight hours, as of the effective date of 
this AD, within 30 days after the effective date of this AD, 
accomplish the requirements of paragraph (i) of this AD.
    (h) For airplanes with 30,000 total flight hours or fewer, as of 
the effective date of this AD, within 90 days after the effective 
date of this AD, accomplish the requirements of paragraph (i) of 
this AD.

[[Page 33397]]

Detailed Visual Inspection, Corrective Action, and Installation

    (i) Perform a detailed visual inspection of the in-tank fuel 
boost pump wire bundles, and applicable corrective actions; and, 
except as provided in paragraph (j) of this AD, install sleeving 
over the wire bundles; in accordance with Boeing Alert Service 
Bulletin 727-28A0126, dated May 24, 1999.

    Note 2: For the purposes of this AD, a detailed visual 
inspection is defined as an intensive visual examination of a 
specific structural area, system, installation, or assembly to 
detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at 
intensity deemed appropriate by the inspector. Inspection aids such 
as mirrors, magnifying lenses, etc. may be used. Surface cleaning 
and elaborate access procedures may be required.

Installation: Possible Deferral

    (j) Installation of sleeving over the wire bundles, as required 
by paragraph (i) of this AD, may be deferred if, within 18 months or 
6,000 flight hours, whichever occurs first, after accomplishment of 
the inspection and applicable corrective actions required by 
paragraph (i), the following actions are accomplished: Perform a 
detailed visual inspection of the in-tank fuel boost pump wire 
bundles, and applicable corrective actions; and install sleeving 
over the wire bundles; in accordance with Boeing Alert Service 
Bulletin 727-28A0126, dated May 24, 1999.

Repetitive Inspections and Corrective Actions

    (k) Repeat the detailed visual inspection and applicable 
corrective actions required by paragraphs (i) and (j) of this AD at 
intervals not to exceed 30,000 flight hours.

Alternative Methods of Compliance

    (l) 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.

Special Flight Permits

    (m) 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

    (n) The actions shall be done in accordance with Boeing All 
Operator Message (AOM) M-7200-99-04035, dated May 21, 1999, or 
Boeing Alert Service Bulletin 727-28A0126, dated May 24, 1999, as 
applicable. 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.
    (o) This amendment becomes effective on June 28, 1999, to all 
persons except those persons to whom it was made immediately 
effective by telegraphic AD T99-12-52, issued on May 24, 1999, which 
contained the requirements of this amendment.

    Issued in Renton, Washington, on June 15, 1999.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-15775 Filed 6-22-99; 8:45 am]
BILLING CODE 4910-13-U