Smiths BOEING B737-100 Guida alla configurazione

Smiths Aerospace

Electronic Systems – Malvern

BOEING B737-100/200/300/400/500 Dec. 18, 2002

DOC NO. 0134ED

Rev: F

DIGITAL FUEL QUANTITY INDICATORS

With

TRANSIENT SUPPRESSION UNIT

MAINTENANCE MANUAL

SUPPLEMENT

Smiths Aerospace

Electronic Systems – Malvern

BOEING B737-100/200/300/400/500

INTRO

Page 1

July 15/02

DOC NO. 0134ED

MAINTENANCE MANUAL SUPPLEMENT

CHAPTER 28 – FUEL

INTRODUCTION

Smiths Aerospace, Inc. designed the Transient Suppression Unit (TSU) to produce an alternate means of

compliance to Airworthiness Directive (AD) 99-03-04 which mandates that operators of Boeing B737

aircraft perform wire separation modification to fuel system wiring. The alternate means of compliance is

achieved by the installation of Smiths Aerospace, Inc. Transient Suppression Units(TSU).

The TSU is inserted in the wiring of the Fuel Quantity Indication System (FQIS) between the in-tank

components (capacitance probes and the compensators) and the Fuel Quantity Indicators located in the

cockpit and refueling stations. The TSUs are installed near where the FQIS wiring enters the tanks and

are intended to prevent any electrical signals, current or voltage, which is capable of igniting fuel vapor,

from entering the fuel tank.

Smiths Aerospace

Electronic Systems – Malvern

BOEING B737-100/200/300/400/500

N=NEW PAGE, *=REVISED PAGE, D=DELETED PAGE

REPRODUCTION OF INFORMATION OR ILLUSTRATIONS CONTAINED IN THE PUBLICATION IS

NOT PERMITTED WITHOUT WRITTEN PERMISSION. LEP

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Dec 18/02

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MAINTENANCE MANUAL SUPPLEMENT

CHAPTER 28 – FUEL

LIST OF EFFECTIVE PAGES

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Smiths Aerospace

Electronic Systems – Malvern

BOEING B737-100/200/300/400/500

N=NEW PAGE, *=REVISED PAGE, D=DELETED PAGE

REPRODUCTION OF INFORMATION OR ILLUSTRATIONS CONTAINED IN THE PUBLICATION IS

NOT PERMITTED WITHOUT WRITTEN PERMISSION. LEP

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Smiths Aerospace

Electronic Systems – Malvern

BOEING B737-100/200/300/400/500

N=NEW PAGE, *=REVISED PAGE, D=DELETED PAGE

REPRODUCTION OF INFORMATION OR ILLUSTRATIONS CONTAINED IN THE PUBLICATION IS

NOT PERMITTED WITHOUT WRITTEN PERMISSION. LEP

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Smiths Aerospace

Electronic Systems – Malvern

BOEING B737-100/200/300/400/500

N=NEW PAGE, *=REVISED PAGE, D=DELETED PAGE

REPRODUCTION OF INFORMATION OR ILLUSTRATIONS CONTAINED IN THE PUBLICATION IS

NOT PERMITTED WITHOUT WRITTEN PERMISSION. LEP

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Smiths Aerospace

Electronic Systems – Malvern

BOEING B737-100/200/300/400/500

TOC

Page 1

July 15/02

DOC NO. 0134ED

MAINTENANCE MANUAL SUPPLEMENT

CHAPTER 28 – FUEL

TABLE OF CONTENTS

SUBJECT

CHAPTER

SECTION

UNIT

PAGE

EFFECTIVITY

Fuel Quantity Indicating System with

Transient Suppression Unit 28-41-04

Description and Operation 1 All

Trouble Shooting 101 All

Removal/Installation, Fuel Quantity

Indicating System 401 All

Removal/Installation, Fueling Quantity

Indicator 403 All

Removal/Installation, Digital

Calibration Trim Unit 405 All

Removal/Installation, Digital

Calibration Trim Unit Cover and Label 408 All

Removal/Installation, V/Ref Totalizer 411 All

Removal/Installation, Fuel Summation

Unit 412 All

Removal/Installation, Transient

Suppression Unit 414 All

Adjustment/Test Configuration 4.1 501 All

Adjustment/Test Configuration 4.2 501 All

Adjustment/Test Configuration 4.3 501 All

Smiths Aerospace

Electronic Systems – Malvern DOC NO.0134ED

MAINTENANCE MANUAL SUPPLEMENT

BOEING B737-100/200/300/400/500

28-41-04

FUEL QUANTITY INDICATING SYSTEM - DESCRIPTION AND OPERATION

1. General (Fig. 1)

A. The fuel quantity indicating system measures the weight of usable fuel in the fuel tanks. Fuel quantity

indicators on the pilots' instrument panel and refuel quantity indicators at the refuel station on the wing

supply visual indication of the fuel weight in each fuel tank. In addition, a fuel summation unit found

on the first officer's auxiliary panel supplies a continuous summation signal input to an on-board

computer where it is converted to an on-demand display of combined tank total remaining fuel or is

used by the computer in various performance parameters. In the No. 1 and No. 2 tanks, five fuel-

measuring sticks are supplied to find the fuel quantity of the applicable fuel tank by mechanical

means.

B. The overall system is composed of a subsystem for each fuel tank, with components found in the

control cabin, in the fuel tank, and at the refuel station on the wing.

(1) Components in the control cabin include a fuel quantity indicator, digital calibration trim unit

(DCTU), and capacitance trimmer (where applicable) for each fuel tank, an indicator test switch

found above the fuel quantity indicators, and a fuel summation unit or V-Reference totalizer

indicator.

(2) Components at the refuel station on the wing include a refuel quantity indicator for each fuel tank

and an indicator test switch. The refuel quantity indicators repeat the fuel quantity shown by the

fuel quantity indicators in the control cabin. The refuel quantity indicators operate only when the

access door for the refuel station is open.

(3) Each fuel or refuel quantity indicator is "universal" - It can be used to supply indication for any fuel

tank; however, a refuel quantity indicator from the refuel panel on the wing cannot be installed in

the control cabin. Likewise, a fuel quantity indicator from the control cabin cannot be installed in

the refuel panel on the wing.

(4) Components In the fuel tanks include a compensator unit and a number of tank units for each fuel

tank. Fuel measuring sticks are installed In the No. 1 and No. 2 tanks. The tank units in each

fuel tank are connected in parallel and positioned so that only usable fuel is measured.

Capacitance values of the tank units in each fuel tank are added to give a single capacitance

value, which is transmitted to fuel quantity indicator.

(5) Components for electrical protection include the Transient Suppression Units (TSU).

The Transient Suppression Unit (TSU), which incorporates a suppression circuit, is designed to

prevent unsafe electrical signals, either current or voltage from entering the fuel tank.

The TSU is inserted in the Fuel Quantity Indicating System wiring between the in-tank

components and the indicator in the cockpit. The suppression unit is mounted near the specific

tank to be protected.

The suppression circuit is placed in series with the fuel measurement signal leads entering the

tank. The protective circuit of the suppression circuit and the Hi-Z shield are grounded to the

aircraft structure via grounding straps and the attaching hardware at its physical location.

Page 1

Apr 19/02

Airplanes with Smiths 2307 Model Fuel Quantity

Indicators with TSU

EFFECTIVITY

Smiths Aerospace

Electronic Systems – Malvern DOC NO.0134ED

MAINTENANCE MANUAL SUPPLEMENT

BOEING B737-100/200/300/400/500

28-41-04

Fuel Quantity Indicating System Component Location

EFFECTIVITY Figure 1 (Sheet 1)

Page 2

Apr 19/02

Airplanes with Smiths 2307 Model Fuel Quantity

Indicators with TSU

Smiths Aerospace

Electronic Systems – Malvern DOC NO.0134ED

MAINTENANCE MANUAL SUPPLEMENT

BOEING B737-100/200/300/400/500

28-41-04

Fuel Quantity Indicating System Component Location

Figure 1 (Sheet 2)

Page 3

Apr 19/02

Airplanes with Smiths 2307 Model Fuel Quantity

Indicators with TSU

EFFECTIVITY

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