[Federal Register Volume 59, Number 103 (Tuesday, May 31, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-13010]
[[Page Unknown]]
[Federal Register: May 31, 1994]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 94-NM-58-AD; Amendment 39-8921; AD 94-11-05]
Airworthiness Directives; Boeing Model 767-200 and 767-300 Series
Airplanes
agency: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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summary: This amendment adopts a new airworthiness directive (AD) that
is applicable to certain Boeing Model 767-200 and 767-300 series
airplanes. This action requires repetitive inspections of the pumping
unit assembly on the override and jettison fuel boost pump assemblies
to detect looseness of the screws that attach the inlet diffuser
assembly to the pumping unit housing, and repair or replacement of the
pumping unit assembly with a serviceable assembly, if necessary. For
certain airplanes, this AD also provides for deactivation of the center
wing fuel tank as an alternative to the repetitive inspections. This
amendment is prompted by reports of failures of the override and
jettison fuel pumps due to damage to impeller units and pumping unit
housings caused by loose diffuser rings in the fuel pump assemblies of
these airplanes. During dry fuel operation, a loose diffuser ring may
cause metal-to-metal contact. The actions specified in this AD are
intended to prevent the generation of sparks and a potential ignition
source inside the fuel tank caused by metal-to-metal contact during dry
fuel pump operation.
dates: Effective June 15, 1994.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of June 15, 1994.
Comments for inclusion in the Rules Docket must be received on or
before August 1, 1994.
addresses: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 94-NM-58-AD, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056.
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 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: Lanny Pinkstaff, Aerospace Engineer,
Propulsion Branch, ANM-140S; FAA, Transport Airplane Directorate,
Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056; telephone (206) 227-2684; fax (206) 227-1181.
supplementary information: The FAA has received reports of failures of
the override and jettison fuel pumps on certain Boeing Model 767-200
and -300 series airplanes. Investigation revealed that the screws that
attach the inlet diffuser assembly to the pumping unit housing became
loose and were ingested into the fuel pump assembly. Loose screws
caused the diffuser ring to become loose and contact the impeller,
which damaged the impeller and pumping unit housing and caused the fuel
pump to seize. During dry fuel pump operation, a loose diffuser ring
also could cause metal-to-metal contact. This condition, if not
corrected, could result in the generation of sparks and a potential
ignition source inside the fuel tank.
The FAA has reviewed and approved Boeing Alert Service Bulletin
767-28A0045, Revision 1, dated April 28, 1994, that describes
procedures for repetitive inspections of the pumping unit assembly on
the override and jettison fuel boost pump assemblies to detect
looseness of the screws that attach the inlet diffuser assembly to the
pumping unit housing, and replacement of the pumping unit assembly with
a serviceable assembly, if necessary. As an alternative to the
inspections, the alert service bulletin also describes procedures for
deactivating the center wing fuel tank. Accomplishment of either of
these actions will prevent the inlet diffuser assembly and various
parts in the pump assembly from creating an ignition source during dry
fuel pump operation.
In addition, the FAA has reviewed and approved Sundstrand Alert
Service Bulletin 5006286-28-A5, Revision 2, dated May 3, 1994, which
describes procedures for repair of the pumping unit assembly.
Since an unsafe condition has been identified that is likely to
exist or develop on other Model 767-200 and -300 series airplanes of
the same type design, this AD is being issued to prevent the generation
of sparks and a potential ignition source inside the fuel tank. This AD
requires repetitive inspections of the pumping unit assembly on the
override and jettison fuel boost pump assemblies to detect looseness of
the screws that attach the inlet diffuser assembly to the pumping unit
housing, and repair or replacement of the pumping unit assembly with a
serviceable assembly, if necessary. For certain airplanes, this AD also
provides for deactivation of the center wing fuel tank as an
alternative for the repetitive inspections. The inspections,
replacement, and deactivation are required to be accomplished in
accordance with the Boeing alert service bulletin described previously.
The repair is required to be accomplished in accordance with the
Sundstrand alert service bulletin described previously.
This AD also requires that operators submit a report of inspection
findings to the FAA.
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
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 notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 94-NM-58-AD.'' The postcard will be date stamped and
returned to the commenter.
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 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 14 CFR part
39 of the Federal Aviation Regulations as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
94-11-05 Boeing: Amendment 39-8921. Docket 94-NM-58-AD.
Applicability: Model 767-200 and -300 series airplanes; line
positions 001 through 473 inclusive, 475 through 504 inclusive, 506
through 532 inclusive, and 534; certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent the generation of sparks and a potential ignition
source inside the fuel tank, accomplish the following:
(a) Within 30 days after the effective date of this AD,
accomplish either paragraph (a)(1) or (a)(2) of this AD, as
applicable.
(1) Perform an inspection of the pumping unit assembly, part
number 5006286 series, on the override and jettison fuel boost pump
assemblies to detect looseness of the screws that attach the inlet
diffuser assembly to the pumping unit housing, in accordance with
Boeing Alert Service Bulletin 767-28A0045, Revision 1, dated April
28, 1994.
(i) If no looseness is found, prior to further flight, identify
the pumping unit assembly with ``28-A5'' next to the part number in
the part number block or other blank space of the identification
plate. Repeat the inspection thereafter at intervals not to exceed
1,000 hours time-in-service.
(ii) If any looseness if found, prior to further flight,
accomplish either paragraph (a)(1)(ii)(A) or (a)(1)(ii)(B) of this
AD; and repeat the inspection thereafter at intervals not to exceed
1,000 hours time-in-service.
(A) Replace the pumping unit assembly with a serviceable
assembly, in accordance with Boeing Alert Service Bulletin 767-
28A0045, Revision 1, dated April 28, 1994. Or
(B) Repair the pumping unit assembly in accordance with
Sundstrand Alert Service Bulletin 5006286-28-A5, Revision 2, dated
May 3, 1994.
(2) For airplanes having a center tank scavenge system: In lieu
of accomplishing the inspection required by paragraph (a)(1) of this
AD, the center wing fuel tank may be deactivated in accordance with
Boeing Alert Service Bulletin 767-28A0045, Revision 1, dated April
28, 1994. The tank may be reactivated only after accomplishment of
the inspection required by paragraph (a)(1) of this AD, and the
repair or replacement, as necessary, required by paragraphs
(a)(1)(ii)(A) and (a)(1)(ii)(B) of this AD.
(b) Within 10 days after accomplishing the initial inspection
required by paragraph (a) of this AD, submit a report of inspection
findings to the Manager, FAA, Transport Airplane Directorate,
Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056; fax (206) 227-1181. The report must
include the inspection results, the airplane line position, the
location of the pump on the airplane, and the number of hours time-
in-service on the pumping unit assembly since new or since its last
removal. Information collection requirements contained in this
regulation have been approved by the Office of Management and Budget
(OMB) under the provisions of the Paperwork Reduction Act of 1980
(44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number
2120-0056.
(c) As of 30 days after the effective date of this AD, no person
shall install an override fuel boost pump assembly, part number
5006283 series, or an override/jettison fuel boost pump assembly,
part number 5009656 series, on any airplane unless that assembly has
been inspected and identified previously in accordance with Boeing
Alert Service Bulletin 767-28A0045, Revision 1, dated April 28,
1994.
(d) 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 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: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Seattle ACO.
(e) 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.
(f) The actions shall be done in accordance with Boeing Alert
Service Bulletin 767-28A0045, Revision 1, dated April 28, 1994; and
Sundstrand Alert Service Bulletin 5006286-28-A5, Revision 2, dated
May 3, 1994. 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.
(g) This amendment becomes effective on June 15, 1994.
Issued in Renton, Washington, on May 23, 1994.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 94-13010 Filed 5-27-94; 8:45 am]
BILLING CODE 4910-13-U-M
