34-15-59a.pdf component maintenance manual

COMPONENT MAINTENANCE

MANUAL . with

ILLUSTRATED PARTS LIST

MAXIMUM ALLOWABLE . AIRSPEED INDICATOR

39948-B2233 39948-B2236

0 Kollsman \ A Divkion ot Sequa Corpor;rtion 220 D.W. Highway, Merrimack, Id. 030544809o(603)889-2500

344559 15 SEPTEMBER 1988

Kollsman COMPONENT MAlNTENANC-E MANUAL

39948-B2233/39948-B2236 .

/ TEMPORARY REVISION NO. 34-l This Tenporary Revision is issued iD not@ users of champs resuning from customer west in accombnce w&h Koikman EC0 31725. insert omsite page 1002,~15-59.

D. Abbreviations

Wherever used, abbreviations are generally in accordance with MILS!CD-12. RF is used to identify refaence callouts, and KO P/N indicates Kollsman Part Number.

E. Vendor Codes

The following is a numerical listing of vendor codes and the name and address of the vendor to which they have been assigned. These codes were obtained hm the latest issue of Cataloging Handbook H41.

Code Vendor Name and Address

VO3508 General Electric Co. Semi-Conductor Products Department W. Genesee Street Auburn, NY 13021

V11262 Moser Jewel Co. 544 Fayette Street P.O. Box 150 Perth Amboy, NJ 0886103727

V11532 Teledyne Relays Teledyne Industries Inc. 12525 Daphne Ave. Hawthorne, CA 90250-3308

v13103

I V53821 V71468

TwDisk 1

Thermalloy Co. Inc. 2021 W. Valley View Lane P.O. Box 810839 Dallas, TX 75381

Qualitair, Inc. 5410 International Parkway Minneapolis, MI 55428

ITT Cannon Division of ITT Corporation 666 E. Dyer Road Santa Ana, CA 92702

34-1 s-59 * Page 1 of 2 Dee 11190

R

r\owman _ . L COMPONENT.MAlNTENANCE MANUAL .

39948-B2233/39948-02236

TEMPORARY REVISION NO. 34-l her? opsite pase IO@, 34-7505Sk

E!!lf Numb-w Number 1 -1 39948-B2233

-IA 3994&B2236

Alrune Udt8 Part Nomencmure Efbct Per Numbat 1234567

.MAxIMuMALLowABLE A 1 AIRSPEED INDICATOR -AIIuIwABLE B 1 AIRSPEED INDICATOR

. 5 18546 MOD INFO NAMEPUWE 1 10 17988 .CALIBRATION STAMP

. 1

15 MS352759211 .SCREW CKO P/N 95003H31) 1 20 38785-6 .CASE & END CAP ASSEMBLY 1

AWACHING PARTS 25 MS352760264 .SCREW (HO P/N 95004H68) 2 '30 19660-2 .wAsHE, Flat 2

-*- 35 400-3 MEMORY INDEX WHITE) 5

(53821) (KO P/N 40151-l) 40 41055-4 .FLANGE, Rear Mounting 1

ATTACHING PARTS 45 95OlOB20 .SCREW,Machine,lOtP 4

Flat head, no. 2-56 x l/4 inch long -*-

50 40726-2 .covER, Lamp 2 ATTACHING PARTS

55 95008B3 .SCREiW,Machine,82" 4 slotted flat head, no. - O-30 x3116inch long -f-

60 42002-30 .BEZEL AND GASKET ASSEMBLY 1 ATTACHING PARTS

9 65 950lOBl9 .SCREW, Machine loo0 Flat 4 head, no. 2-56 x W16 inch long -*-

'70 38775-30 ..BEZEL 1 75 39637 ..GASKET 1 80 MS9021-040 -PACKING, Preformed 1

(Ko P/N 90300-7) 85 37900-3 iDOUBLE WIZDGE WINDOW

ASSEiMBLY 1 90 MS90680041 -PACKING, Preformed 1

(Ko P/N 90300-5) 95 41954-l LAMP, T-3/4, 5V (Modified) 4

(DSlthruDS4) 100 MS90680148 .PACKING, Preformed 1

(KO P/N 90300-6) 105 21634 JILTER 1 110 24297 .scREw, Pitot fitting 1

---- - - - -- -_ - _ ---- ---- - -- _- _ - - ITEM NOT ILLUSTRATED TWDisk 1

Detailed Parts List

Kollsman COMPONENT MAiNTENANCE MANUAL

39948-82233139948-82236

RECORD OF REVISIONS . .

REVISION ISSUE DATE REVISION ISSUE DATE NUMBER DATE INSERTED BY NUMBER DATE INSERTED BY

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RECORD OF TEMPORARY REVISIONS

TEMPORARY ISSUE REV. NO. DATE

DATE DATE 1 INCORP. I REMOVED INSERTED i REpf@jED qt# c?8 BY *-.-

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COMPONENT MAINTENANCE MANUAL 39948-82233139948-82236

SERVICE BULLETIN LIST

Incorp. Service 6ulletin Incorp.


39948-82233139948-82236

LIST OF EFFECTIVE PAGES '

Subject Page . ..a.

, Title Page

Record of Revisions RR-1

Record of Temporary Revisions RTR-1

Service Bulletfn List SBL-1

List of Effective LEP-1 Pages LEP-2

Table of Contents TC-1

Date

sep Imii

Sep 15188

Sep 15188

Sep 15188

Sep 15188 Sep 15188

Sep 15188

Introduction INTRO-1 Sep 15188

Description and 1 Operation 2

3 4

Testing and Fault Isolation

101 102 103 104 105 106 107 108 109 110 111 112 113 114 115 116 117 118 119 120 121 122

Sep 15188 Sep 15188 Sep 15188 Sep 15188

Sep 15188 Sep 15188 Sep 15188 Sep 15f88 Sep 15188 Sep 15188 Sep 15188 Sep 15188 Sep 15188 Sep 15188 Sep 15188 Sep 15188 Sep 15188 Sep 15188 Sep 15188 Sep 15188 Sep 15188 Sep 15188 Sep 15f88 Sep 15188 Sep 15188 Sep 15188

Subject

Dtsassembly

Cleaning

Check

Repair

Assembly

Page Date

301 302 303 304 305 306

401 402 403 404

501 502 503 504

601 602 603 604 605 606 607 608

Sep 15188 Sep 15188 Sep 15188 Sep 15188 Sep 15188 Sep 15188

Sep 15188 Sep 15188 Sep 15188 Sep 15188

Sep 15188 Sep 15188 Sep 15188 Sep 15188

Sep 15188 Sep 15188 Sep 15188 Sep 15188 Sep 15188 Sep 15188 Sep 15188 Blank

701 Sep 15188 702 Sep 15188 703 Sep 15188 704 Sep 15f88 705 Sep 15188 706 Sep 35188 707 Sep 15188 708 Sep 15188 709 Sep 15188 710 Sep 15188 711 Sep 15188 712 Sep 15188 713 Sep 15188 714 Sep was 715 Sep 15188 716 Sep 15188 717 Sep 1988

hny reproduction of the information or illustrations contained in this publication is not permissible without specific approval of Kollsman.

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LEP-1 Sept 15188

Kokman COMPONENT MAINTENANCE MANUAL

3994808223313994842236

LIST OF EFFECTIVE PAGES

Subject Page

718 719 720 721 722 723 724 725

Date Subject Paqe_ - Date

. 726 727 728 729 730

'Sep Sep 15188 15188

Sep 15188 Sep 15188

Sep 15188 Sep 15188 Sep 15188 Sep 15f88 Sep 15188 Sep 15188 Sep 15188 Sep 15188 Blank

Fits and Clearances 801 802

Special Tools, Flxtures, and Equipment

901 902

Sep 15188 Sep 15188

Sep 15188 Blank

Illustrated Parts Llst

1001 Sep 15188 1002 Sep 15188 1003 Sep 15188 1004 Sep 15188 1005 Sep 15188 1006 Sep 15188 1007 Sep 15188 1008 Sep E/88 1009 Sep 15188 1010 Sep 15188 1011 Sep 15188. 1012 Sep 15188 1013 Sep 15188 1014 Sep 15188 1015 Sep 15188 1016 Sep 15188 1017 Sep 15188 1018 Sep 15188 1019 Sep 15188 1020 Sep 15188 1021 Sep '15188 1022 Blank

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Any reproduction of the information or illustrations contained In this publication IS not permlssfble without specific approval of Kollsman.

1401G LEP-2 Sept 15188

Kolkrnan COMPONENT MAINTENANCE MANUAL

39948082233/3994%82236

TABLE OF CONTENTS

Lkscriptlon and Operation . . . . . l . . . . . . . . . . Testing and Fault Isolation . . . . . l . . . . . . . . . Automatic Test Requirements (Not Applicable) e Disassembly . . . . . . . . . . . . . . . . . . . . . . . Cleaning . . . . . . . . . . . . . . . . . . . . . . . . Check.......................... Repair . . . . . . . . . . . . . . . . . . . . . . . . .

. Assembly Fits and Cie&&e;

. . . . . . . l . . . . . . . . . . .

. . . . . . l . . Special Tools, Fixtu;e;,'and'Equjpre~t. . . . . . . . . . Illustrated Parts List. . . . . . . . . . . . . . . . . .

; 101

301 401 501 601 701 801 901

1001

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COMPONENT MAINTENANCE MANUAL 39948082233139948-82236

Introduction

A . General

Thi.s GXUW&~ contains OV@rtiaUi tamponent maintenance procedures with i llustratt2 parts WA 53~ !+hmum Allowable Airspeed Indicator, P/N 39948-82233, manufactured by Kollsman, 220 Daniel Webster Highway, Merrimack, New Hampshire 03054-4809. ?

6 . Additional Models

Overhaul procedures for similar models which are included in this manual are the same as those recommended for the initial type, except L for the specific differences noted on the applicable pages. This includes the following model with its corresponding effectivity code that is used throughout this manual.

Model No. Code Symbol

39948-82236 A

NOTE: Code symbol/a\is used for the basic model 39948.B2233, where necessary for clarification.

C . Related Publications

Installation and Operating Instructtons Publication Number S1396.

14OlG Introduction-

34-15-59 Sep:N:%l


. 1 . Description and OperatIm

A . Purpose

The Maximum Allowable Airspeed I:!!caic;ak?r Uw~lnafte~ referred to as the fndtcator) ts designed to provide alrspeed indication, maximum allowable airspeed indlcatton, overspeed warning switch closure stgnal, and lowspeed warntng switch closure signal In a single instrument.

6 . Description (See Figure I>

The indicator is a 3ATI size clamp and panel-mounted Instrument. (See Table 1 for leading particulars). Its dlspiay consists of a white airspeed pointer and a black, white, yellow, and green striped Vmo/Mmo pointer agatnst a common 50 to 300 kno black dial wtth white numerals and graduations. On indicator coded Lk the dial also has a white arc from 88 to 150 knots, a red graduation at 100 knots, and a blue graduation at 120 knots. An IMI ring with five white memory indices is mounted to the Indicator bezel. The indices have a moveable range from 50 to 300 knots and can be set by the pilot for any reference point as desired. The entire dlsplay Is illuminated by four S-volt blue-white lamps.

C. Operation

Airspeed indications are derived from the expansion (with increasing pitot pressure> and contraction of a differential pressure capsule. This capsule motion is transmitted through a l'ink to a sector'shaft and then to the atrspeed pointer.

e

The Vmo/Mmo function is derived from the motion of an aneroid capsule which is actuated by static pressure introduced within the Instrument case. Capsule response to varying static pressure is transmitted via linkage through another sector shaft and gear shaft to the VmolMmo

~-pointer. Capsule displacement is calibrated to the specificatiofi- Vmo/Mmo characteristic curve of the SUPER JETSTREAM 31 aircraft.

An internal lonspeed switch '52," whose contacts are open at and below 135 knots, is connected to an internal underspeed relay 'X2." The relay Is then connected to an external lowspeed warning indicator that is located within the aircraft. Above 135 knots the lowspeed switch contacts will close, energizing the underspeed relay. When energized, the underspeed relay provides a closed set of contacts for the external warning indicator at pins 31-A and Jl-6. When the remotely mounted PRESS TO TEST button is pushed, the underspeed relay deenerglzes which opens the contacts at pins 31-A and 31-B.

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39948082233/39948-82236

Table 1 Leading Parti culats

Dial: I A White numerals and graduations on a black background ?

A White numerals and graduations on a black backgroufid, white arc 88 to 150 knots, red graduation at 100 knots, and blue graduation at 120 knots

- A/S Pointer: White Vmo/Mmo Potnter: Black, white, yellow, and green Power I@OFF1' Flag: Orange

PHYSICAL CHARACTERISTICS:

Form: Length: Width: Height: Weight: Bezel: Case:

ARINC #408-3ATI Approximately 5.36 inches Approximately 3.26 inches Approximately 3.26 inches 2.0 pounds maximum Black Black

RANGE:

(1) Airspeed: 50 to 300 knots (2) Altitude: -1,000 to +25,000 feet

LIGHTING:

Integral SV ac; color: blue/white

INPUTS :-- --

(1) Static pressure (MS33649r5) (2) PItot pressure (MS33649r4) (3) 28V dc power energizes OFF" flag solenoid and relays (4) Push-to-Test switch in series with 28V dc power

OUTPUTS: -

(1) Overspeed warning switch closure signal occurs when A/S pointer approaches Vmo/Mmo speed.

0 Lowspeed warning switch closure signal occurs at and above 135.knots. (3) "OFF" flag comes into view when 28V dc power is lost or Press-to-Test

button !s pushed.

ELECTRICAL CONNECTOR:

Ms3114H12-6P mates with @3126F-12-8s

39948082233 39948-82236

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39948-82233139948-82236

The internal Vmo/Mmo overspeed switch '51," whose contacts are closed at safe speeds, is connected to an internal overspeed relay rNKl.ll 2 This relay is connected to dn external overspeed warning indicator that 1s also located within the aircraft. At ant above CY~S~~~~C!, ?%

' cverspeed switch contacts open and deenergize the ~~verot;)e~I relay. __ When deenergized, the overspeed relay will provide a ctoseii jet of ' contacts for the external warning indicator at pins Jl-C and Jl-0. Upon pushing the PRESS TO TEST button, the overspeed relay will deenergize and close pins Jl-C and Jl-0:

Kollsrnan COMPONENT MAINTENANCE MANUAL

39948~82233/39948-82236

1 l Testing a Fault Isolation

A . General

.

This s~~tim contalr;s sperY:~ checks and tests to determine the condition of the indicator or most probable cause of its malfunction. Performance of these checks and tests will determine the extent of disassembly required without completely tearing down and rebuilding an indicator that has been removed from service. If the unit does not meet the test requirements, refer to the troubleshooting procedures in paragraph M. to isolate the fault. If the unit passes all tests, return it to service.

B . Test Conditions

(1) Atmospheric Conditions

Unless otherwise specified, all tests shall be conducted at an atmospheric pressure of 29.92 in. Hg abs ~0.6 in. Hg at an ambient temperature of +2YC #C (+77*F 29'F). When tests are conducted with the atmosphere and temperature substantially dlfferent from these values, proper allowances shall be made for any variations. Relative humidity should not exceed 90 percent.

(2) Standard Pressures

The Airspeed, Mach Number, and Altltude Tables are based on Technical Note D-822 and U.S. Standard Atmosphere 1962.

(3) Attitude

Unless otherwise specified, all tests shall be made with the instrument In its normal operating position, dial vertical.

(4) Vibration

Unless otherwise specified, light vibration or tapping shall be applied to the indicator case to remove friction before any test read1 ngs are taken.

(5) Test Setup

Figure 101 shows the test setup required for bench testing the indicator. Equipment required to test the indicator is listed in Table 101. Equivalent equipment may be substituted.

(6) Test Results

Table 102 consists of test data sheets to be used to record the results of the tests performed in this section.

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Kollsman

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COMPONENT MAINTENANCE MANUAL 39948082233/39948-82236

D.C. POWER SUPPCBY

(POWER MATE)

I Pl,

3994882233

*FABRICATE CAKE SEE FIGURE 102 - _.

Test Setup Figure 101


Table 101 Test Equipment and Materials

Equipment/Material D?scPipttoc

Adapter Cable (Fabricate using Figure 102)

Connects indlcatoi to Test Fixture P/N 36578

D.C. Power Supply Power Mate Model BP-400

*

Provides dc power to operate Test Ftxture P/N 36578

Range: 0-SOV dc Accuracy: zO.SV dc

Precision Pressure Controller-Monftor Provides a means to control or measure Kollsman P/N 18905810000 altitude pressure applied to UUT

Test Fixture Kollsman P/N 36578

Provides power and controls to test Indicator

Variable Autotransformer Superior Model 116B

Provides ac power to operate lights during Hghting tests

Range: O-12OV ac

Table 102 Test Data Sheet

Indicator Serial Number Date

C . Visual Inspection: ACCEPT REJECT

Paint .......................................... Damage ......................................... Memory Indices .......... ........................

Wlndow Cleanliness .................................... Chips - Scratches .............................. Coating . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

DWlay Characters Cleanliness .................................... Paints ......................................... Coordination of Elements .......................

EQ 1 Cleanliness .................................... Shell Damage ................................... Pins (Straightness) ............................ Marking ........................................

_-.

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Kollstnan COMPONENT MAINTENANCE MANUAL

39948.82233/39948-82236

Table 102 (Cont'd) Test Data Sheet

C . Vtsual Inspection: (CantiS . .- KCEPT REJECT

Static Connector Entrance Port.................................. * Threads........................................ Screen.........................................

Pitot Connector Entrance Port..................................

. Threads........................................ Plates

D .

E .

F .

a

G .

H .

Nameplate ...................................... Mod Plate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Calibration Decal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Safety Wire Damage ......................................... Loose .......................................... Missjng ........................................

Llghting Test

1 . 4 Lamps illuminated 2 . Lamp color is blue/white

"OFF" Flag Test

1 . Flag out of view with power applied 2 . Flag In view with power removed

Push to Test

1 . Power "OFF" flag comes fnto view 2 . Pins A/B open 3 . Pins C/D closed

Leak Test (Pitot Pressure)

1 . Reading after stabilization 2 . Reading after 1 minute 3 . Difference

Leak Test (Static Pressure/Case Leak)

1 . Reading after stabilization 2 . Reading after 1 minute 3 . Difference

knots knots knots

feet feet feet

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39948~8223313994842236


I. AIrspvrrl Scale Error and Frtctlon Test

Seal e Error *Friction

Pohter Reading Pointer Pointer

Airspeed After Reading Reading Pi tot Tapping Diff Scale Error Before After Friction Pressure (Knots) Mnots) Tolerance Tapping Tapping Diff Tolerance (Knots) Up Down Up Down (ZKnots) (Knots> (Knots) (Knots) (zKnots>

50 60 +

70 80

100 +

120 140 150 + 160 + 180 200 +

220 240 250 +

270 280 300 *

*Friction Test Points a

3 2 2 2 2 2 2 25 . 3 3 3 3 3 3 3 35 . 35 .

xxx xxx

xxx xxx xxx xxx

xxx

xxx xxx xxx xxx

3 xxx xxx 3 xxx xxx 3 3 xxx 3 xxx xxx 3 xxx xxx 3

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39948082233/39948-82236


3 0 +zximum Allowable Airspeed Scale Error, Hysteresis, *?vxi After E'Tfect Test

Tolerance

A UP UP Diff Down ' Diff. Allow For

Alt . Nominal Reading Reading Before Friction Reading Up & Hysteresis Ft Knots Before After & After Toler. xl600 (+O/-8) Tapping Tapping Tapping Allow

After - Down & After Tapping Reading Effect

.

0 23 5 23

10 23 15 23 16.4 23 20 21

xxx xxx xxx 4 xxx xxx +3(b) zxx

+2(a) Fxx xxx

xxx xxx xxx 4 4

xxx xxx

xxx xxx

xxx xxx xxx xxx xxx xxx 25 196 4

(a) Hysteresis Test (b) After Effect Test Pofnts (1 minute wait)

+2(a)

A/C Mmo = .477 MACH

Tolerance

A UP UP Diff Down Diff. Allow For '

Alt. Nominal Reading Reading Before Friction Reading Up & Hysteresis Ft Knots Before After & After Toler. xlt)OO (+O/-8) Tapping Tapping Tapping Allow

After Down & After Tapping Reading Effect

0 249 5 249

10 249 15 - 249 16.4 249 20 234 25 211

xxx xxx

xxx

xxx

xxx xxx

xxx 4 xxx 4 4 xxx 4

xxx

xxx xxx xxx

xxx xxx xxx xxx

+3(b) zxx +2(a) Fxx

_--

xxx xxx +2(a)

(a) Hysteresis Test (b) After Effect Test Points (1 minute wait>

A/C Mmo = 513 MACH

3994842233 39948-82236

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39948-82233139948-82236

Table 102 KontW Test Data Sheet

Test * /A Altftude

Feet VmO (x 1000) (+6/-O) Knots Reading Mmo in MACH and KNOTS Reading

* 0 231 xxx xxx xxx 5 231 xxx xxx xxx

10 231 xxx xxx xxx 15 231 xxx xxx 16.4 231 xxx xxx xxx 20 xxx xxx l 477 +.01/-O 217 +6/-O 2s xxx xxx . 477 +.01/-O 196 +6/-O

Operational at 35,000 feet ACCEPT REJECT

Overspeed warning switch activation cannot occur until the IAS pointer is coincident or above the MAAS pointer reading.

ACCEPT REJECT

A :%ude Feet VmO (x 1000) (+6/-O> Knots Reading Mmo in MACH and KNOTS Reading

0 249 xxx xxx xxx - 5 249 xxx-- -.- xxx xxx 10 249 xxx xxx xxx 15 249 xxx xxx 16.4 249 xxx xxx xxx 20 xxx xxx .513 +.01/-O 234 +6/-O 25 xxx xxx . 513 +.01/-O 211 +6/-O

Operational at 35,000 feet ACCEPT REJECT

Overspeed warning switch activation cannot occur until the IAS pointer is coincident or above the MAAS pointer reading.

ACCEPT REJECT

39948-82233 399WB2236

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COMPONENT MAINTENANCE MANUAL 39948-B2233/39948-82236

Table 102 Kont'd) Test Data Sheet

1 . Switch closes at and above * 135 knots for increasing speed.

2 . Switch opens below 135 knots for decreasing speed.

C . Visual Inspection

(1) Check the indicator for any signs of obvious damage. Check the rear mounting flange for cracks or scratches in the paint. Verify that the indicator has five white memory indices and that they move smoothly 360' around the face of the indicator.

(2) Check the window for cleanliness, scratches, chips, and any other signs of damage.

(3) Check the display elements for cleanliness, patnt condition and color, and for coordination of elements.

(4) Check connectors for cleanliness, pin straightness (electrical>, shell damage, thread condition, and any other damage.

(5) Check the condition of all nameplates and decals and verify that data are correct.

t

(6) Verify that the safety wire on the rear of the Instrument is present and is not loose or damaged.

_. -

D . Lighting Test

(1) Connect the Variable Autotiansformer to indicator at pins "G" and rIH'4 of the 'W1g connector.

(2) Apply power to the indicator and adjust the autotransformer output voltage to 5.0 +O.lV ac.

(3) Verify that all four lamps (two in each upper corner) are illuminated and ire blue/white in color. Record results.

(N Turn power to indicator off and disconnect test setup.

E . OFF Flag Test

(1) Connect the indicator to Test Fixture PIN 36578 as shown in Figure 101.

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COMPONENT MAINTENANCE MANUAL 39948~82233139948-82236

OPDT TOGGLE SWITCl4 CUITLER-HAMMER

P/N 7S92U7*

PI OR EOUIVALENT

t e A 1 8 C 1 D

MS3126-12-8s MATES WITH

31 OF INDICATOR

MS3114H-1208P MATES WITH

TEST FiXTURE PIN 36678

AVAILABLE FROM: EATON CORPORATlON AEROSPACE & COMMERCIAL CONTROlS OlVtStON 35 BEDFORD STREET LEXINGTON, MA 02173

Adapter Cable Schematic Figure 102

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39948-82233139948-82236

(2) Apply power to the indicator and verify that the OFF flag disappears from view. Record results.

(3) Remove power fx?m t&K; Irid!catov ana b connector open to ambient pressure.

(2) Apply pressure to the indicator until the IAS pointer reads 300 knots, then clamp off the pressure applied to the indicator.

(3) After the indicator reading stabilizes, read and record the indicated airspeed.

- (-4) Wait one minute; then read and record the indicated airspeed again.

(5) Calculate and record the difference between the two readings. There shall be no apparent difference between the two readings.

(6) Return the PPC-M to ambient pressure and disconnect test setup as desired.

H . Leak Test (Static Pressure/Case Leak)

(1) Connect the indicator and test equipment as shown in Figure 101 and apply a pressure equal to 23,000 feet to both ports using a "Y" connector.

(2) Clamp off the pressure applied to the indicator and, after stabilization, read and record the indicated altitude.

B (3) Wait one minute; then read and record indicated altitude again.

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39948082233/39948-82236

(4) Calculate and record the difference between the two readings. The dffference shall not exceed 100 feet.

(5) Return the PPC-M to ambient pressure, and discafmx% ck tact: setup as desired. - r

I . Airspeed Scale Error and Friction Test l

(1) Connect the indicator's pitot (P) connector ;o the PPC-M as shown in Figure 101. Leave the static (5) connector open to ambient pressure. Observe throughout this test that pointer motion is smooth- without hunting, oscillation, or excessive sticking and

. jumping.

(2) Apply pressure to the indicator equal to the first test pressure listed In section I of Table 102, being careful not to overshoot the test point.

(3) After vibration and stabilizat!on, read and record the airspeed indication.

(4) Calculate and record the difference between the IAS pointer reading and the test pressure listed in the table.

(5) The scale error reading must be within the tolerance indicated in the table.

(6) Repeat steps (2) through (9 for the remaining test points listed in the table.

(7) Repeat steps (2) through (6) for the test points listed in the table in a decreasing direction.

(8) Return the PPC-M to ambient pressure.

(9) Apply pressure to the indicator equal to the ffrst friction test pressure listed in section I of Table 102, being careful not to overshoot the test point.

(101 Read and record the airspeed lndlcation, then after vibratjon and stabilization, read and record the airspeed indication again.

(11) Calculate and record the difference between the two readings. This reading must be within the tolerance indicated in the table.

(12) Repeat steps (9) through (11) for the remaining test points listed in the table.

(13) Return the PPC-M to ambient pressure and disconnect the test setup as desfred.

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Kolisrnan COMPONENT MAINTENANCE MANUAL

39948-82233139948-82236

J . Maximum Allowable Airspeed Scale Error, Hysteresis, and After Effect Test .

(1) Connect the indicator and test equipment 3~ C_!IWC !g Figure 101. Observe throughout this test that all ;;ointer mkiem is moot;? - without hunting, oscillation, or excessive :tSrk'nc '?;j jum$~(y.

(2) Apply pressure to the indicator equal to the. first test pressure listed in section 3 of Table 102, being careful not to overshoot the test point.

(3) After vibration and stabilization, read and record the MAAS * pointer indication.

(4) The reading must be within the tolerance indicated in the table.

(5) Repeat steps (2) and (3) for the remaining test points listed in the table but prior to vibration, read and record the MAAS indication if applicable.

(6) Calculate and record the difference between the two readings. The dtfference must be within the tolerance indicated in the table.

(7) Hold the test pressure at 25,000 feet for between 5 and 15 minutes. During this time read and record the MAAS indication.

(8) Increase the test pressure (decrease altitude) at a rate of approximately 3,000 feet per minute till you reach 10,000 feet.

(9) Hold the test pressure at 10,000 feet for between 1 and 10 minutes. During this time, read and record the MAAS indication.

(10) Further increase the pressure at a rate of 3,000 feet per minute until reaching a reading of 0 feet.

ill) Hold the test pressure at 0 feet for at least 1 minute but not more than five minutes. During this time, read and record the MAAS tndication.

(121 Calculate and record the difference between the readings taken In steps (7) through (11) and the "UP READING BEFORE TAPING" for the same test points. The difference must be within the tolerance indicated in the table.

(13) Return the PPC-M to ambient pressure and disconnect the test setup as desired.

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39948-82233139948-82236

K . Overspeed Warning Test

. (1) CCV-+ the indicator and test equipment as shown in Figure 101. .

F&e 9Y?a' CXI rnt= fabricated cable in the position to monitor the %vERsPEFD CN~BIS: ; i gnal . Observe throughout this test that overspeed warning switch activation does not occur until the IAS pointer is coincident with or above the UAAS pointer reading.

(2) Apply pressure to the indicator equal to the first test pressure listed in section K of Table 102.

(3) Verify that the light on the tester illuminates when the IAS . pointer reaches the value listed in the table. Record results.

(4) Repeat steps (2) and (3) for the remaining test points listed in the table.

(5) Apply pressure to the indicator equal to 35,000 feet.

(6) Verify that the indicator is still operational at this altitude. Record results. .

(7) Return the PPC-M to ambient pressure and disconnect test setup as desired.

L . Lowspeed Warning Test

(1) Connect the indicator's pitot (P) connector to the PPC-M as shown in Figure 101. Leave the static (9 connector open to amblent pressure. Place '51" on the fabricated cable in the position to monitor the "LOWSPEED" output signal.

(2) Apply pressure to the indicator until the IAS pointer reaches 150 knots.

(3) - Verify that when the pointer reaches l-35 ~3 knots, the 1 tght on the tester illuminates. Record results.

(41 Adjust the pressure applied to the indicator until the IAS pointer returns to 0 knots.

(9 Verify that when the pointer reaches 135 +3 knots, the light on the tester extinguishes. Record results.

(6) Disconnect test setup as desired.

M . Troubleshooting

Troubleshooting involves the detection and location of the causes of faulty operation 0 f the unit and undertaking the proper remedial action. Most operational difficulties have definite symptoms that serve as clues to the cause of the problem. Table 103 lists some probable causes and corrections for several possible malfunctions. Schematic diagram Figure 103 is provided to aid in troubleshooting. z

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Kollsman l COMPONENT MAINTENANCE MANUAL

39948082233139948-B2236

Table 103 Troubleshooting Chart -& Y

Troubit! Probable Cause Correction

iahttng Test

(1) Lamp fails to illuminate, or wrong color

.

VFF" Flau Test

(1) Flag does not operate properly

Push to Test

(1) Flag does not come into view

(2) Outputs at pins A/B t or C/D incorrect

Leak Test (Pltot Pressure)

(1) Excessive Pitot Leakage

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(a) Defective or wrong type lamp (95, IPL, Fig. 1)

(b) Defective wiring or electrical connection

(a) Defective drum indicator (SOS, IPL, Fig. 2)

(b> Defective wiring or electrical connection

Fig. 1)

(a) Defective drum Indicator (505, IPL, Fig. 2)


(a) Defective printed wiring board assembly Al (145, IPL, Fig. 1)


(a> Loose pitot screw (110, IPL, Fig. 1)

(b) Defective preformed packing (140, IPL,

(a) Check lamp (95) and replace if necessary.

(a) Check using Figure 103 and repair as required.

(a> Check continuity of indicator and replace if necessary.

(a) Check using Figure 103 and repair as required.

(a) Check continuity of indicator and rep1 ace if necessary.

(a> Check using Flgure 103 and repair as required.

(a) Check using Flgure 103 - and repair or replace as required.

(a) Check using Flgure 103 and repair as required.

(a) Tighten screw (110).

(a) Check preformed packing (140) and replace iif necessary.

homtnan COMPONENT MAINTENANCE MANUAL

39948~82233139948~82236

Table 103 Kontd) Troubleshooting Chart

Trouble Correction

Leak Test (Pftot Pressure) (ContW ?

(1) (Cont'd)

.

W Defective A/S cap- (a> Replace capsule sule assembly (60, assembly (60) and IPL, Fig. 2) recalibrate indicator

in accordance with the applicable procedure in the "ASSEMBLY*' section.

Leak Test (Static Pressure/Case Leak)

(1) Excessive case (a> Loose rear mounting (a) Tighten machine screws 1 eakage flange (40, IPL, (45).

Fig. 1) (b) Loose bezel and (a) Tighten machine screws

gasket assembly (60, (65) l IPL, Fig. 1)

tc) Defective bezel (a) Check bezel gasket gasket (75, IPL, (75) and replace in F1g. 1) accordance with para-

graph G of REPAIR section if necessary.

cd> Defective preformed (a) Check preformed packing packings (80, 90, (80, 90, and 100) and and 100, IPL, Fig. 1) replace if necessary.

(e) Connector 31 (120, (a) Ttghten nut (P/O 120) IPL, Fig. 1) loose which secures

--(f)- Loose case and end -- connector 31. cap assembly (20, (a) Tighten screws (25). IPL, Fig 1)

(g) Loose lamp covers (a) Tighten machine screws (SO, IPL, Fig. 1) (55) 0

(h) Defective sealing (a) Check sealing surfaces surfaces of case and end cap

assembly (20, IPL, Fig. 1). rear mounting flange (401, and bezel and gasket assembly (60) for dirt, scratches, br deformation.

(b) Clean, straighten warped parts, and smooth out scratches if possible.

W Replace items that are damaged beyond repair.

*

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Kollsman .

COMPONENT MAINTENANCE MANUAL 39948082233139948~82236

b

Table 103 (Cont'd) Troubleshooting Chart

Trouble Correction

Airweed Scale Frror and Friction Test .

(1) Scale Error readings (a> Loose pointer (a) Check pointer i20) and vary ertatlcally. assembly (20, reposition as required. Pointer hunts and

-oscillates IPL, Flg. 2)

(2) Scale Error readings (a) Excessive endplay, (a) Check and reset in within to1 erance but loose gear mesh, or accordance with Table pointer hunts and improper hairspring 801 as necessary. oscillates tension

(3) Pointer sticks and (a) Gear teeth of A/S (a) Check gear teeth and jumps as pressure is sector gear assembly clean, deburr, or re- changed (205, IPL, Fig. 2) place parts as necess-

and pinion (335) ary. contaminated, burred, or damaged

(b) Airspeed link assem- (a> Check link for freedom , bly (55, IPL, Fig. 2) of movement and adjus' binding as necessary.

cc> Defective or con- (a) Check jewel of jewel taminated jewel and holder assembly bearings and bearing (135, IPL, Fig. 2) and surfaces rocking shaft assembly

(235) and clean, lubricate, or replace as required. ----

(d> Interference between (a) Check position of windings of spring and arbor assembly (230, IPL, Fig. 2)

spring and arbor assembly (230) and adjust as necessary.

(4) Consistent difference (a> in excess of specified tolerances for readings taken with pressure increasing and pressure decreasing

(5) Scale error readings (a) Gear mesh between within tolerance only MS sector gear if indicator is tapped assembly (205, IPL, or vibrated. Fig. 2) and pinion (Excessive frlctlon) (335) too tight

Excessive capsule hysteresis

(a> Replace A/S capsule assembly (60, IPL, Fig. 2) and recalibrate in accordance with the applicable procedure ln *'ASSEMBLY" section.

(a) Check gear mesh and adjust as necessary.

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39948-82233139948-82236

Table 103 Kontd) Troubleshooting Chart

. . Trouble Probable Cause

Airspeed Scale Error and Friction Test (Cont'd)

(9 Kont'd)

c

(b> Insufficient endplay on A/S rocking shaft assembly (-145, IPL, Fig. 2)

cc> Cracked or contaminated jewel bearings

(d) Damaged or contaminated pivots

(e) Airspeed link (a) Check link for free- assembly (55, IPL, dom of movement and Fig. 2) binding adjust as necessary.

(6) Consistently low (a) Pitot leakage readings, error spread increasing as pressure increases

* (7) Airspeed indications (a) Pointer assembly consistently high or (20, IPL, Fig. 2) low with no change position has as indicator fs tapped shifted or vibrated (b) Arm and pin assembly

(210, IPL, Fig. 2) improperly adjusted

(8) Airspeed indications (a) Indjcator out of exceed specified calibration tolerances with no set pattern. Tapping or vibrating indicator does not change reading

?

(a) Check and adjust endplay in accordance with Table 801 as required.

(a) Check jewel of jewel and holder assembly (135, IPL, Fig. 2) and rocking shaft assembly (235) and clean, lubricate, or replace as required.

(a) Check pivot assembly (125, IPL, Fig. 2) and pivot of rocking shaft assembly (239 and clean or replace as required.

(a) Check pitot leakage in accordance with procedures listed under "Leak Test (Pitot Pressure)" of this table.

(a) Check pointer (20) and reposition as required.

(a) Check and recalibrate indicator in accordance with the applicable procedure in "ASSEMBLY" section as required.

(a) Recalibrate indicator in accordance with the applicable procedure fn "ASSEMBLY" section.


Table 103 Kont'd) Troubleshooting Chart

Trouble Probable Cause

Maximum Allowable Airspeed Scale Error. Hysteresis. and After Effect Test

(1) Scale Error readings (a) Loose MAAS marker (a> Check marker assembly vary erratically. assembly (25, IPL, (25) and reposition Pointer hunts and Fig. 2) as requl red.

.oscillates

(2) Scale Error readings (a) Excessive endplay, (a) Check and reset In within tolerance loose gear mesh, accordance with Table but pointer hunts and or improper 801 as necessary. 0x1 llates hairspring tension

(3) Pointer sticks and (a) Gear teeth of MAX (a) Check gear teeth and jumps as pressure is sector gear assembly clean, deburr, or changed (180, IPL, Fig. 2) replace parts as

and pinion and collar necessary. assembly (340) contaminated, burred, or damaged

(b> Gear teeth of sector (a) Check gear teeth and gear assembly (300, clean, deburr, or : IPL, Fig. 2) and replace parts as marker shaft pinion necessary. (430) contaminated, burred, or damaged

(c) Defective or con- (a) Check jewel of jewel taminated jewel and holder assembltes bearings or bearing (135 and 250, IPL, Fig. surfaces 2) and jewel of rocking

shaft assemblies (235 . and 305) and clean, lubricate, or replace as required.

(d) Interference between (a) Check position of windings of spring spring and arbor and arbor assemblies assemblies and readjust (230, 285, and 415, as necessary. IPL, Fig. 2)

- . _

(4) Consistent difference (a) Excessive capsule (a> Replace altitude in excess of specified hysteresis capsule assembly tolerances for readings (105, IPL, Fig. 2) taken wlth pressure and recalibrate in increasing and pressure accordance with the decreasing applicable procedure

. / in lNASSEMBLY" section. Q

14OlG '


39948-82233139948-82236

Table 103 (Cont'd) Troubleshooting Chart

Probable Cause Correction

Maximum Allowable Airspeed Scale Error, Hysteresis, and After Effect Test Kont'd)

(5) Scale Error readings (a) Gear mesh between (a> within tolerance only MAX sector gear

1 if indicator is tapped assembly (180, IPL, or vibrated. Fig. 2) and pinion (Excessive friction) and collar assembly

(340) too tight (b) Geai mesh between (a)

sector gear assembly (300, IPL, Fig. 2) and marker shaft pinion (430) too tight

(c) Insufficient endplay (a) on A/S rocking shaft assembly (-145, IPL, Fig. 2) or altitude rocking shaft assembly t-260)

(d) Cracked or contami- (a) nated jewel bearings

Check gear mesh and adjust as necessary.

Check gear mesh and adjust as necessary.

Check and adjust endplay in accordance with Table 801 if required.

Check jewel of jewel and holder assemblies (135 and 250, IPL, Fig. 2) and jewel of rocking shaft assemblies (235 and 309 and clean, lubricate or replace as requi-red. -

(e) Damaged or (a) Check pivot assembl!es contaminated pivots (125 and 240, IPL,

Fig. 2) and pivot of rocking shaft assemblies (235 and 305) and clean or replace as required.

(6) Maximum allowable (a) MAAS marker assembly (a) Check marker assembly airspeed indicators (25, IPL, Fig. 2) (29 and reposition consistently high or position has shifted as required,. low with no change as indicator is tapped or vibrated

14OlG

Kollsman .


Table 103 (Cont'd) Troubleshootlng Chart

Troe,b F e Probable Cause Correction

Maximum Allowable Alrsbeed Scale b Hvsteresis, and A t

T-or. fter Effect Tw (Cont.'d)

(7) Maximum allowable airspeed indkations

- exceed tolerances with no set pattern. Tapping or vibrating indicator does not change reading

Overspleed Warninu Teqt

(1) Light on tester does not illuminate

(2) Light on tester illuminates but

$ airspeed readings out of tolerance

LowsDeed Warninu Test

(1) Light on tester does not illuminate

(a> Indicator out of calibration

(a) Recalibrate indicator. in accordance with the appllcabl e procedure in "ASSEMBLY" section.

(a) Defective wiring (a) or electrical connection

(b) Defective printed (a) board assembly Al (145, IPL, Fig. 1)

W Contact spring of (a) MAX sector gear assembly (180, IPL, Fig. 2) not touching contact screw of A/S sector gear assembly (205)

Check using Figure 103 and repair as required.

Check using Flgure 103 and repair or replace as required. Check and reposition ' sector gear assemblie: (180 and 205) In accordance with Table 801 .

(a) Indicator out of calibration

(a) Recalibrate Indjcator in accordance with applicable procedure In 'NASSEMBLY*1 section.

(a) Defective wiring or (a) Check using Figure 103 electrical connection and repair as required.

(b) Defective prfnted (a) Check using Figure 103 wiring board assembly and repal r or replace Al (14, IPL, Fig. 1) ds required.

cc> Contact spring of A/S (a) Check and repositlon sector gear assembly * A/S sector gear (205, IPL, Fig. 2) assembly (209 as not touching terminal necessary. of contact and holder assembly (480) .

1401G-


Table 103 Kont*d> Troubleshckting Chart

Correction

Lowsneed. Warninu Test Kont'd)

(2) Light on tester illuminates but airspeed reading

- out of tolerance

(a) Indicator out of calibration

(a) Recalibrate indicator In accordance with applicable procedure in "ASSEMBLY" section.

140lG

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COMPONENT MAINTENANCE MANUAL 39948~82233139948~82236

1 .

IJQTE: See TESTING AND FAULT ISOLATION sectton to esb.Nish the condi- tlon of the altimeter or most probable cxuse of ~lhnal*~~~~~c~i~~ This is to determine the extent of disassen&?v required i+!thwt completely tearing down and rebuilding the altimeter.

A General * .

(1) Dlsassembly should be limited to the extent necessary for repair, replacement, cleaning, or adjustment of the altimeter. It is suggested that all parts and assemblies be stored separately (and logically) in clean compartmented plastic containers upon removal.

(2) Procedures are in order of disassembly from the highest to the lowest subassembly or part. Disassemble only as far as indicated by the nature of the fault. The dtsassembly procedures should not be performed as a part of routine maintenance. The order of dtsassembly of electronic equipment can usually be determined by inspection. Special techniques, cautions, warnings, and unique procedures, when required, are In this sectlon.

(3) Use accepted instrument shop procedures during all disassembly operations.

6 . Precautions and General Techniques

WHEN UNSOLDERING ANY SOLID-STATE DEVICES (ICS, TRANSISTORS, CAUTION: OR DIODES), USE A TEMPERATURE-CONTROLLED SOLDERING IRON WITH A 600WATT MAXIMUM RATING AND A HEATSINK TO PREVENT HEAT DAMAGE.

(1) Tag or otherwise Identify all electrical wiring prior to disconnecting. Take note of wire color codjng, placement and lead dress, and methods of applying insulation before unsoldering

__- .- or removing any electrical parts. _. -.-

(2) Whenever damage 1s found, associated parts should be checked to determine its source, cause, and extent.

(3) When removing parts or assemblies that have a specific relationship to other parts or subassemblies, place a mark between the two that will facilitate realtgnment of the two during reassembly or calibration.

(4) Although the removal and replacement of jewel bearings is described throughout the following procedures, for completeness, It is not recommended that these bearings be moved unless they have been damaged and need replacement or unless movement is required to perform a disassembly or assembly operation.

1401G


39948-82233139948-82236

(5) Replacement of gaskets and preformed packing is recommended whenever the surfaces they seal are disturbed during disassembly

I protedures.

NOTE: Due to the'lndetermtnate ttme p~fods be+yzo: inCl;;ment djsassembly, actual replacement of gaskets and preformed packings may be based on in-service experience.

(6) As a general procedure applicable to disassembly of the instrument after it has been removed from the case, tag and Identify all hardware removed using appropriate Illustrattons. ALWAYS observe and make sketches or notes of the positlon of the wiring harness and wire tape BEFORE cutting lacing cord ties and unsoldering electrical connections. Tag all leads that must be unsoldered in order to Indicate both their wire routing and their destinations. In reassembly of the instrument, follow the same routing of wfring harnesses and wiring tapes as was used In the instrument before disassembly. This procedure is essential to avoid possible interference of wiring with moving parts of the instrument.

C . Maximum Allowable Airspeed Indicator (See IPL, Fig. 1)

(1) If replacement Is necessary, remove mod info nameplate (5) and calibration stamp (10) from case and end cap assembly (20).

(2) Remove safety wire from screw (15) and two screws (251, then remove screw (15) from case and end cap assembly (20).

(3) Remove case and end cap assembly (20) by removing two screws (29 and two flat washers (30).

(4) Remove five memory Indices (35) from rear mounting flange (40).

(5) - Remove rear mounting flange (40) from-bezel and gasket assembly (-601 by removing four machtne screws (45).

(6) Remove two lamp covers (50) from bezel and gasket assembly C-60) by removing two machine screws (55) each.

(7) Remove bezel and gasket assembly (-60) from mechanism assembly (200) by removing four machine screws (65).

NOTE: Do not separate bezel (70) and gasket (75) unless replacement of gasket . (75) is necessary.

(8) Remove preformed packing (801, double wedge wlndow assembly (851, and preformed packing (90) from previously removed bezel and gasket assembly C-60).

(9) Remove four lamps DSl through OS4 (95) from sockets in mechanism assembly (200). .

1401G

-_ --_- - -_-_ -

COMPONENT MAINTENANCE MANUAL 39948062233/39948-B2236

(10) Remove preformed packing (1001, filter (1051, and pitot flttlng screw (110) from rear chamber (130).

. 4 1-l 1 !&IS@.! zkr ~9 remove the two wires attached to terminals 10 and A S

on the t'ear sSa2 of terminal board assembly TN (190).

(12) Unplug connector P2 025) from connector 32 (5, IPL, Fig. 3). remove hex nut (P/O 120, IPL, Fig. 1) from ionnector 31 (120), and remove harness assembly (-115) from rear chamber (130).

NOTE: Do not remove connector Jl (120) from connector P2 (125) unless replacement Is necessary.

(13) Remove rear chamber (130) from mechanism assembly (ZOO) by removing three screws (139, then remove preformed packing (140) from pitot fitting (P/O 60, IPL, Fig. 2).

(14) Unplug connector P3 (180, IPL, Fig. 11, from connector 33 (5, IPL, Fig. 31, then remove printed wiring board assembly Al (145, IPL, Fig. 1) from mechanism assembly (200) by removing three each cap screws (1501, lockwashers (1551, and flat washers (160X.

(15) Unsolder and remove the eSght wires attached to the front side of the terminal board assembly TBl (190).

(16) Remove harness assembly (-165) from mechanism assembly (ZOO) by removing two cap screws (170) and two lockwashers (175).

NOTE: Do not separate connector P3 (180) or diode CR1 (185) from terminal board assembly TBl (190) unless replacement is necessary.

(17) Unscrew three chamber mounting posts (195) to remove them from mechanism assembly (200).

D . Mechanism Assembly (See IPL, fig. 21 -

(1) Remove retainer assembly (5) from frame assembly (580) by temovlng three shoulder screws (10) and three spacers (15).

(2) Carefully remove pointer assembly (20) and MAAS marker assembly (25) from their respective shafts.

(3) Remove three dial screws (351, then remove dial (30) and shield (40).

(4) Remove clip (45) and pin (50) from A/S capsule assembly (701, then remove IAS link assembly (55) from between A/S capsule assembly (70) and arm and pin assembly (210).

(5) Remove AIS capsule assembly (60) and capsule clamp (65) by removing two cap screws (70).

1401G


(6) Remove clip (75) and pin (80) from altitude capsule assembly (1051, then remove altitude link assembly (-85) from between aW+ude capsule assembly (105) and arm and p'ln asseibly 2651.

N;)TE; ,UO not remove jewel (90) or endstone (95) from altitude link (100) unless replacement Is necessary.

(7) Remove altitude capsule assembly (105) and cgpsule clamp (110) by removing two cap screws (115).

(8) Remove wedge (1201, then loosen setscrew (130) and remove pivot I assembly (125).

(9) Loosen setscew (140) then remove A/S rock frame assembly (580)

remove jewel and holder assemb ing shaft and sector assembly L

(10) Loosen setscrew (155 1 and remove counterweight (150) calibrating arm clamp (160).

(11) Remove cap screw (165) and remove calibrating arm clamp (160) from rocking shaft assembly (235).

(12) Loosen two setscrews (175) and remove collar clamp (1701, sector gear assembly (180) and steel washers (185 and 190) from rocking shaft assembly (235).

WE Record the number of steel washers (185 and 190) removed to facilitate reassembly.

(13) Loosen two setscrews (2001, then remove collar clamp (195) and airspeed sector and gear assembly (205) from rocking shaft assembly (235).

- f-14) Loosen setscrew (215) and remove arm-and pin assembly (210) from calibrating arm clamp (220).

05) Remove cap screw (2251, then remove calibrating arm clamp (220) and spring and arbor assembly (230) from rocking shaft assembly (235).

(16) Loosen machine screw (560) to facilitate the removal of altitude rocking shaft assembly C-260).

(17) Loosen setscrew (245) and remove pivot assembly (240).

(18) Loosen setscrew (2551, remove jewel and holder assembly (2501, then remove altitude rocking shaft assembly C-260) from frame assembly (580).

1401G

(19) Loosen setscrew (270) and remove arm and pin assembly (265) from calibrating arm clamp (275)..

COMPONENT MAINTENANCE MANUAL 39948082233139948~82236

(20) Remove* cap screw (280). then remove callbtating arm clamp (275) and spring and arbor assembly (285) from rocking shaft assembly (305).

. I 6 (21) bOWl two setX?ews (i?%),j thn remv2: collar clamp (290) and

sector gew assembiy i&X0. from rocking shaft assembly (305).

(22) Loosen setscrew (315) and remove bearing and housing assembly (310) from rear bearing housing assembly (395).

.

(23) Loosen machine screw (360) to facilitate the removal of hairspring (320).

(24) Loosen two setscrews (3301, then remove hairspring (320>, collar clamp (3251, and pinion (335) from pointer shaft assembly (350).

(25) Loosen four setscrews (3451, remove pinion and collar assembly (340) from pointer shaft assembly (3501, then withdraw pointer shaft assembly (350) from marker shaft assembly (465).

(26) Remove spring clamp (355) from rear bearing housing assembly (395) by removing machine screw (360) and flat washer (365).

(27) Remove wedge (3701, then remove spring clamp (375) from rear bearing housing assembly (395) by removing machine screw (3801, lockwasher (3851, and flat washer (390).

(28) Remove rear bearing housing assembly (395) from frame assembly (580) by removing two each cap screws (4001, lockwashers (4051, and flat washers (410).

(29) Loosen two setscrews (4251, then remove spring and arbor assembly (415) and collar clamp (420) from marker shaft assembly (465).

(30) Loosen two setscrews (4401, then remove marker shaft pinion (430) - - . - and collar clamp (435) from Marker shaft assembly (465).

(31) Loosen setscrew (450) and remove calibration arm (445) from calibration arm clamp (455).

(32) Remove cap screw (460) and remove calibration arm clamp (459 from marker shaft assembly (465).

(33) Withdraw marker shaft assembly (465) from frame assembly (580).

(34) Remove capsule support and A/S contact assembly (-470) from frame assembly (580) by removing three machine screws (475).

NOTE: Do not remove green wire from contact and holder assembly (480) or separate contact and holder assembly (480) from capsule support (500) unless replacement is necessary.

I 14OlC f f 4


39948-82233139948-82236

(35) Remove drum indicator (505) from indicator support (525) by .' 5, removing one each: cap screw (5101, lockwasher (SlS), and flat

washer !55&. g t z

(36) Remove indbtor sq~ori: iz25; trom frame- assembly (580) by removing one cap screw (530) and one lockwasher (53%

(37) Remove A/S sector stop (540) from frame assel;rbly (5801 by removing one cap screw (545) and one lockwasher (550).

(38) Remave spring clamp (555) from frame assembly (580) by removing . * one cap screw (560) and one lockwasher (56%

(39) If necessary, remove screw (570) and hex nut (575) from frame assembly (580).

E . Printing Wiring Board Assembly Al (See IPL, Figure 3)

(1) Remove lacing tape used to secure connector wiring to printed wiring board drilling (70).

(2) Remove two connectors 32 and 33 (5) with associated wiring from printed wiring board drilling (70) by unsoldering the 14 wires (seven on each side) attached at printed wiring board drilling (70).

NOTE: Do not unsolder two connectors 32 and 53 (9 from their associated wiring.

(3) Unsolder and remove electrical components (10 through 40) from printed wiring board drilling (70).

(4) Unsolder and remove two relays Kl and K2 (45) from printed wiring board drilling (701, then remove two mounting pads XKl and XK2 (50) from the two relays (45).

(5) Unsolder and remove two transistors Ql and Q2 (55) from printed wiring board drilling (701, then remove two mounting pads XQl and XQ2 (60) from the two transistors (55).

Nm: Do not remove three standoffs (65) from printed wiring board drilling (70) unless replacement is necessary.

14OlG

normnan COMPONENT MAINTENANCE MANUAL

39948-82233139948-82236

1 . Cleaninq

A . General I .

(1) Cleaning Materials, Table 401, conta;n~~~~C.Ttesls Mxzessar~ tc -accomplish the cleaning procedures outllnszf !rr tMz seMr5. Equivalent items may be substituted for those listed.

(2) Use accepted instrument shop procedures during all cleaning procedures.

. Table 401

Cleaning Materials

Material Source

Freon TF

Cobehn Spray - Clean Solvent

Spray-type cleaning equipment

Alcohol, isopropyl FSTT-I-735A (for cleaning double window wedge assembly)

Brush, soft (watchmaker's no. 4)

Brush, moderately stiff (watchmaker's no. 2)

* Tissue, lens (silicone treated)

Swab, cotton

Cloth, soft, lint free

Eraser, artgum, soft

Tweezers

E.I. Oupont DeNemours & Co. Germay Park Wilmington, DE 19898

Cobehn Inc. 226 Passaic Ave. Fairfield, NJ 07006

Commercially available






Commercially avaf lable

Commercially available * .


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Kollsfnan COMPONENT MAINTENANCE MANUAL

39948-62233139948-62236

(3) With the indicator disassembled to the extent necessary to l accomplish required correcttve action, use the following

-. procedures, as applicable, for cleaning of parts. I/ L 1 *: * 'as,1 4.1. .rt I .I"." ' " * * "V.* ;r: '- " WARNING: VAPORS FROM CLEANING 1;OcVEldfl: kRE HARMFUL. CjSZ ONLY b

. . 4 ns < ,WITH AOEQUATE VENTILATICJN. !S'OID ~YXd;!G&D XZATHING OF VAPORS. AVOID PROLONGED OR REPEATED CONTACT WITH SKIN. ?

6 . Painted Surfaces

(1) All painted surfaces except the display elements (pointer assemblies, dials, and drum indicator) should be cleaned with a I soft cloth or brush moistened if necessary, with Freon TF.

(2) Display elements (pointer assemblies, dtals, and drum indicator) should be cleaned by gentle application of a soft artgum eraser. Remove residue with compressed air at 20 to 30 psi.

C. Sealing Surfaces

(1) Remove all traces of vacuum grease and foreign matter from seallng surfaces of bezel and gasket assembly (60, IPL, Fig. 1) and mechanism assembly (200) with a so stiff brush Mstened with Freon TF.

(2) Clean sealing surfaces of case and end chamber (130) using the procedure prev (1) .

(3) Clean sealing surfaces of rear chamber

t c

cap ous

0th or a moderately

assembly (20) and rear y described in step

(130) and pltot flttlng (PI0 ZOO> using the procedure previously described in step (1).

D . Fllter (105, IPL, Fig. 1)

(11 Clean filter with a moderately stiff brush moistened with Freon TF . Dry with clean, dry, compressed air of 30 psi or less. *

E . Double Wedge Window Assembly (85, IPL, Fig. 1)

CAUTION: DO NOT USE EXCESSIVE AMOUNTS OF CLEANING FLUID, NOR APPLY IN A MANNER THAT COULD RESULT IN FLUID SEEPING INTO SPACE BETWEEN WEDGES. DO NOT USE ANY ABRASIVE CLEANING MATERIAL.

(1) To prevent streaking when relatively large viewing surfaces are cleaned, progressively clean a series of smaller, overlapping areas until complete coverage is obtained.

(a) Wipe a relatively small area using a lens tissue moIstened with isopropyl alcohol and immediately wipe dry With a clean lens tissue.

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Kollsman COMPONENT MAINTENANCE MANUAL . 39948.82233139948-82236

(b) Repeat this procedure as necessary until surfaces are properly cleaned and free of streaks.

F . Electrical Components

0) Clean electrical components with a soft brush.

NOTE: If dirt is difficult to remove, use clean, dry, compressed air at a pressure of 30 psi or less.

(2) Remove dirt and dust from electrical connectors and terminals using a moderately stiff brush moistened with Freon TF.

1 (3) Remove flux residue after soldering using a swab moistened with a

small amount of alcohol.

G . Mechanical Parts

(1) Clean jewels and bearing holes with spray-type cleaning equipment and spray clean solution as follows:

(a) Adjust compressed air supply to a pressure of 80 psi. This must be maintained for the duration of the cleaning procedure.

(b) Allow five to six minutes for cleaning equipment components to warm up prior to any cleaning operation. Maintain temperature of air at +154"F (69'0, measured l/4 inch from nozzle tip.

W Use tweezers or forceps to hold part in warm air stream, approximately S/16 to l/2 inch from nozzle. Preheat for two to five seconds.

(d) Spray part with cleaning solvent for five to six seconds, then dry with warm air stream.

NOTE: Do not flood part with cleaning solvent. A series of short sprays of solvent followed by drying. periods will produce best results.

(e) Inspect part for cleanliness when dry and, if necessary, repeat this procedure.

(2) Clean gear teeth with a moderately stiff brush and 'Freon TF. .

(3) Clean pivots with a lint free cloth moistened with Freon TF.

CAUTION: HANDLE A/S CAPSULE ASSEMBLY (60, IPL, FIG. 2) AND ALTITUDE CAPSULE ASSEMBLY (105, IPL, FIG. 2) WITH EXTREME CARE AS THEY MAY BE EASILY DAMAGED.

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39948-82233139948-82236

(4) Clean A/S capsule assembly (60) and altitude capsule assembly (105) as follows:

(a) Clean capsule assembly using the procedure previously described in paragraph G.(l)(a) through G.(l)(d). ,

(b) Inspect capsule assembly for cleanliness when dry and, if necessary, repeat this procedure. ?


1. Check

A. General

After the indicator has been disassembled to the extent required, use the following information as a guide for the inspection of parts, where applicable. Where damage or excessive wear is evident, check the associatsd parts to determine the source and extent'of damage or wear.

NOTE: Do not disassemble solely for the purpose of Inspection. The extent of disassembly should be governed by data obtained in "TESTING AND FAULT ISOLATIONS section. Check associated parts . where damage is evident.

B . Corrective Action

(1) Repair or replace defective parts and recheck tolerances, fits, clearances, and calibration as required.

(2) Table 501 lists equipment required to accomplish check procedures in this section. Equivalent substltutes may be used for items 11 sted..

Table SO1 Check Materials, Tools, Fixtures and Equipment

Equipment * Source

D.C. Power Supply Mode 1 BP-400

Power Mate Co. 2727 Kurtt Street San Diego, CA 92110

Eye Loupe (10X> Commercially available

Variable Auto Transformer Model 11613

Superior Electric Co. 383 Middle Street Bristol, CT 06010

VOM Model 630A

Triplett Corp. One Triplett Drive Bluffton, OH 45817

l .

C . Visual Inspection

.

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(1) Inspect all -parts for wear or damage and determine their servicea- bility for reuse. Rejected items may be repaired or replaced as conditions warrant. When damage or excessive wear is evident, check mating parts to determine source and extent of defect. Remedial action should be taken to correct existing or impending malfunctions. Use Table 502 as a guide for inspecting disassembled parts.


39948082233/39948-82236

Table 502 Visual Inspectlon

Part Inspection

A/S Capsule Assembly (60, IPL, Fig. 2) and Altitude Capsule Assembly (105, IPL, Fig. 2)

A/S Sector Gear Assembly (205, IPL, Fig. 2) and Sector Gear Assembly (300)

Case and End Cap (20, IPL, Fig. l), Rear Mounting Flange (40). Lamp Cover (SO), Bezel (701, and Rear Chamber (130)

Connectors (120, 125, and 180, IPL, Fig. 1) and (5, IPL, Fig. 3) Double Wedge Window Assembly (85, IPL, Fig. 1)

Drum Indicator (505, IPL, Fig. 2)

Electrical Components

Filter (105, IPL, Fig. 1)

Gaskets (75, IPL, Fig. 1) and Preformed Packings (80, 90, 100, and 140, IPL, Fig. 1)

?Hairspring (320, IPL, Fig. 2) and Spring and Arbor Assembly (230, 285, and 419

Jewels

Ptns, Shafts, Pivots and Links

Pinion (335, IPL, Fig. 21, Pinion and Collar Assembly (3401, and Marker Shaft Pinion (430)

Pointer Assembly (20, IPL, Fig. 21, MAAS Marker Assembly (251, and Dial (30)

Nicks, dents; corrosion, or scratches

Damaged contact springs, burred, broken or bent teeth, bent or deformed sectors

Scratched surfaces, dents, or damage to sealing surfaces

Bent pins, cracked insulation, dirt, and foreign matter Cracks, scratches, dirt, chips

Dents, scratched or bent drum surface, paint

Damaged containers, charred or discolored surfaces

Tears, clogging

Proper fit, swelling, cuts, and nicks

Bent, damaged, or distorted windlngs

Scratches, cracks, loose settings, foreign particles inside jewel assemblies

Bent or damaged areas, excessive wear

Burrs, broken or bent teeth, surface defects, corrosion

Distortion, paint damage

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39948~82233139948-82236

Table 502 Kont'd) Visual Inspection

Part Inspectton

Printed Wiring Board Assembly Dirt, cracks Or chips, damage to (145, IPL, Fig. 1) components

Screws and Nuts Stripped, burred, or nicked . threads

Terminal Board Assembly Dirt, cracks or chips, damage to (190, IPL, Fig. 1) terminals .

Wiring Broken leads, damaged or discolored insulation, frayed edges on wire tape leads

0. General Check Procedures

(1) Examine A/S capsule assembly (60, IPL, Fig. 2) and altitude capsule assembly (105) for kinks, dents, or apparent distortion.

(2) Inspect bearings, bushlngs, and jewels for chips, cracks, or scratches and for evidence of out-of-round condition. Eye loupe (10X) inspection is recommended.

(3) Check pivots for bent shafts, bent or broken tips, corrosion, excessive wear, and nicks or scratches on the bearing surface.

(4) Check balance of pointer assembly (20, IPL, Fig. 2) and math marker assembly (2%

(5) Check all internal and external machine threads for stripping, cross-threading, or other damage.

(6) Inspect condition of double wedge window assembly (85, IPL, Fig. 1) . There shall be no chips, scratches, or abrasions.

(7) Filter (105, IPL, Fig. 1) inside static connection at the rear of the instrument should be free of-dirt or other contaminations. Remedy or replace as necessary. .

(8) Check gaskets, sealing rings, and preformed packing for proper fit .

(9) Check to see that all links, pins, and shafts are straight and free from excessive wear.

(10) Inspect gears and sectors for burrs, corrosion, and bent or broken teeth.

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39948~82233139948~82236

E l Electrical Check Procedure

(1) Inspect internal wiring for defects or damage. Check for worn insulation and evidence of overheating.

(2) Check for continuity by consulting electrical schematic.

(3) Inspect all connectors and sockets for loose, bent, or broken pins and for cracked or otherwise damaged inserts and shells.

(4) Examine prlnted wiring board assembly (145, IPL, Fig. 1) for * cleanliness, cracks, chips, and loose or damaged components.

(5) Check all electrical components and assemblies for proper operation and to verify that they are within specification.

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A . General

(1) Repair, for the most part, constitutes replacement with new pads. Repair where conditions warrant; replace all worn, damaged, or questionable items. All soldering operations shall incorporate 63/37 type solder and noncorrosive flux. Alcohol (MILTA-6091) may be used to clean up residual flux upon coolIngi. Use accepted instrument shop procedures during all repair operations. Information concerning areas for which repair is deemed practfcal is given below. Table 601 lists materials required for repair.

(2) A small arbor press should be used for removal and replacement of press fit items and for staking where necessary.

8 . Gears

(1) Normally, the repair of gears is limited to replacement with a new part. However, depending upon the extent and location of the damage, minor repairs can be made to bring these items within serviceable limits.

(a> Minor scratches or burrs on the flat of a gear tooth can be polished out with a fine india stone. Minor scratches, which do not hamper structural strength or function, can, in most cases, be ignored.

(b) Chipped gear teeth shall be cause for rejection unless the chip Is at one end of the gear tooth and will still allow full meshing surface with mating gear and not contribute to friction. In such cases, the chip may be dressed with a fine india stone.

C . Wiring

(1) Replace damaged wiring with wire of the same size and color coding.

(2) Use 63/37 solder and noncorrosive flux to make wiring connections. After soldering, remove flux residue with a swab moistened with alcohol.

D . Gaskets and Seals

(1) Experience dictates replacement of these Items at time of overhaul.

4

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39948082233139948-82236

Table 601 L

Repair Materials, Tools, Fixtures and Equipment

Material Source

Anvil

Arbor Press

Gasket Cementing Mask KO P/N T38105-001

Gasket Applicator KO P/N T38105-002

India Stone

Jewel Punch .

Staking Tool Kit

Ace tone

Alcohol (MIL-A-6091) Commercially available

Freon TF E.I. DuPont De Nemours and Co. Chemicals and Pigments Dept. Customer Service Center Brandywine Bldg. 15th Floor Wilmington, DE 19898

Moisture and Fungus Proof Varnish (Conformal Coating) (MIL-V-1736)

Noncorrosive Flux (MIL-F-14256)

Pressure Sensitive Adhesive, #75

Soft Lint-Free Cloth

Solder, SN63 (Fed. Spec. QQ-S-571)

Flat Black Baking Enamel, Color 37038 (Fed. Std. 595)


Commercially available -

Koll sman 220 Daniel Webster Highway Merrimack, NH 03054

Kollsman 220 Daniel Webster Highway Merrimack, NH 03054





Plasti-Kote Co. Medlna, OH 44256


Minnesota Mining 8t Mfg. Co. Adhesives, Coatings & Sealers Div. 3M Center St. Paul, MN'%lOl-1428



Randolph Products 92 North 12th Street Carlstadt, NJ 07072-2851

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Documents

34-15-59a.pdf component maintenance manual