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

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]

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