Eaton Aerospace LLC 

Fuel and Motion Control Systems Division 

3675 Patterson Ave S.E. 

Grand Rapids, Michigan 49512 

U.S.A.

SERVICE BULLETIN 

REVISION TRANSMITTAL SHEET 

NOTICE TO HOLDERS OF SERVICE BULLETIN 692D100-52-4, ORIGINAL ISSUE, DATED 

SEPT 13, 2012,REVISION 1, DATED JAN. 21, 2013 AND REVISION 2, DATED AUGUST 01, 

2013.

Subject: Revision 3 to SB 692D100-52-4 

Date: August 14, 2014 

COMPLIANCE INFORMATION RELATED TO THIS REVISION 

NOTE: Additional work is required on 692D100-13 actuators that have been modified in accordance with 

service bulletin 692D100-52-4, Original Issue, dated September 13, 2012 or Revision 1, dated 1/21/13. 

NO additional work is required on 692D100-13 actuators that have been modified in accordance with 

service bulletin 692D100-52-4, Revision 2, dated 08/01/13. 

Comments from operators and Eaton Aerospace have initiated this revision to further identify affected units by serial 

number. 

Specific changes to text or graphics are identified by vertical revision bar(s) located adjacent to the change. Specific 

changes incorporated into Revision 3 are as follows: 

Page Paragraph 

Affected Description of Change 

ALL Updated ALL page footers to reflect Revision 3 

2 Table 1 Corrected S/N range within Table, added S/N 2257B. 

REVISION HISTORY 

Original Issue: Sept 13/12 

Revision 1: Jan 21/13 

Revision 2: Aug 01/13 

Revision 3: Aug 14/14 

PAGE EFFECTIVITY 

1 through 17 Aug 14/14 

Revision Transmittal Sheet 

Page 1 of 1 
767/777 Aircraft 

SERVICE BULLETIN

692D100-13 Actuator

Original Issue –SEPTEMBER 13, 2012 692D100-52-4

Revision 3: AUGUST 14, 2014 Eaton 2013. All rights reserved. Page 1 of 17 

Large Cargo Door - Rotary Actuators – Rework & Re-Identification of 

Actuators 

1. Planning Information 

A. Effectivity: 

Units Affected: 

 Eaton Part Number Boeing Part Number Keyword 

 692D100-13 S135W132-3 Actuator 

Serial Numbers – Serial number, - for P/N 692D100-13 rotary actuators as listed in 

Table 1 below have been reworked by Eaton Aerospace to incorporate AMS 9310 

matched gear sets or were originally manufactured with AMS 9310 matched gear sets. 

The units listed in Table 1 require re-identification per paragraphs 3. B and 3. C. herein. 

All other 692D100-13 actuators not identified in Table 1 are addressed in paragraph 3. D 

herein. 

Table 1. 692D100-13 Actuators with AMS9310 Steel Matched Gear Sets 

257B 1137B 1321B 

310B - 311B 1145B - 1146B 1337B 

334B 1162B 1348B 

375B 1170B - 1171B 1351B - 1352B 

394B - 395B 1192B 1355B 

456B 1194B 1361B 

515B 1198B - 1199B 1369B 

555B 1205B 1373B 

568B 1216B 1386B 

578B 1235B 1388B 

692B 1242B 1391B - 1392B 

920B - 922B 1245B - 1246B 1394B 

929B 1249B 1417B 

974B - 975B 1252B 1419B 

986B 1255B 1425B 

1024B 1260B - 1261B 1432B 

1026B 1269B 1437B 

1031B - 1032B 1271B 1440B - 1441B 

1033B - 1034B 1280B 1463B 

1065B 1284B - 1285B 1467B 

1075B 1300B 1471B - 1472B 

1088B 1302B 

1100B 1307B 

1109B - 1111B 1309B 

1118B - 1120B 1316B - 1317B 
767/777 Aircraft 

SERVICE BULLETIN

692D100-13 Actuator

Original Issue –SEPTEMBER 13, 2012 692D100-52-4 

Revision 3: AUGUST 14, 2014 Page 2

Use or disclosure of data contained on this page is subject to the restriction on the first page of this document

Table 1. 692D100-13 Actuators with AMS9310 Steel Matched Gear Sets- continued 

1488B - 1489B 2436B 2827B 

1492B 2438B 2829B 

1516B 2454B 2845B 

1583B 2456B 2855B 

1590B 2463B 2861B 

1613B 2475B 2907B – 3022B 

1626B 2456B 3024B – 3053B 

1632B 2463B 3055B – 3135B 

1646B 2475B 3137B – 3813B 

1670B - 1672B 2483B 3815B – 6178B 

1685B 2493B 6180B – 6182B 

1697B 2506B 6186B 

1721B 2509B 

1726B 2563B 

1755B 2580B 

1757B 2660B - 2662B 

1901B 2665B 

1906B 2667B 

1915B 2678B 

1933B 2685B 

1940B 2697B 

2002B 2705B 

2057B 2712B 

2115B 2723B 

2120B 2725B 

2170B - 2171B 2732B 

2203B 2735B 

2229B 2740B 

2230B 2747B 

2234B 2749B 

2239B 2756B - 2757B 

2257B 2771B 

2279B - 2280B 2778B 

2292B 2781B 

2309B - 2310B 2788B 

2317B 2798B 

2318B 2800B 

2322B - 2323B 2807B 

2350B 

2406B 2821B 
767/777 Aircraft 

SERVICE BULLETIN

692D100-13 Actuator

Original Issue –SEPTEMBER 13, 2012 692D100-52-4 

Revision 3: AUGUST 14, 2014 Page 3

Use or disclosure of data contained on this page is subject to the restriction on the first page of this document

B. Concurrent Requirements – None 

C. Reason: 

Eaton Aerospace has been made aware of several incidents where the actuator did not 

function as required during operation (i.e. un-commanded lowering). Upon further 

investigation, the cause was found to be excessive gear wear on the first-stage sun gear 

(output gear of the no-back assembly). Excessive wear of one 692D100-13 actuator may 

cause higher than designed loading on the remaining actuator. Preliminary investigation 

revealed that this condition is most likely to affect actuators exceeding 12,000 flight 

cycles on 767 aircraft. This condition presents a possible safety hazard and could result 

in a dispatch delay. By performing the actions described in this service bulletin, product 

reliability will be enhanced. 

D. Description: 

This Service Bulletin provides instructions in three sections. The first two sections provide 

instructions for re-identification of rotary actuators using a compliance plate and also remarking of the unit ID plate for the identified serial numbers listed in Table 1 herein. The 

third section provides instructions for disassembly, replacement of the ball detent matched 

set and 1st stage planetary gears and re-assembly of the rotary actuators. Upon 

completion of these actions, the rotary actuator shall be re-identified. 

E. Compliance 

Actions listed in this Service Bulletin should be accomplished at the earliest opportunity 

when manpower and facilities are available. 

F. Approval: 

The repairs and modifications herein comply with the applicable regulations and are on 

record with the supplier as FAA-approved, as well as EASA/JAA approved. 

G. Manpower: 

Estimated time requirements are as follows: 

Accomplishment: (Para. 3. A., B. and C. - On-Aircraft Section) 1 hour (Approx.) 

Accomplishment: (Para. 3. A. and D. - Off-Aircraft Section) 6 hours (Approx.) 
767/777 Aircraft 

SERVICE BULLETIN

692D100-13 Actuator

Original Issue –SEPTEMBER 13, 2012 692D100-52-4 

Revision 3: AUGUST 14, 2014 Page 4

Use or disclosure of data contained on this page is subject to the restriction on the first page of this document

H. Weight and Balance: Performance of this Service Bulletin will not affect unit weight. 

I. Electrical Load Data: Not Affected 

J. Software Accomplishment Summary – Not Applicable 

K. References 

1) Existing Data: 

Component Maintenance Manual – 52-34-02- Revision 13 or later 

SL692D100-01 – Eaton Service Letter 

2) Data supplied with this Service Bulletin: 

None 

3) Reference Boeing Service Bulletin 767-52A0100 

4) Reference Boeing Service Bulletin 777-52-0053 

L. Other Publications Affected 

Component Maintenance Manual - 52-34-02- Revision 13 or later 

M. Interchangeability or Intermixability of Parts 

No component of Ball Detent Matched Set, P/N 692C181-1 shall be authorized 

for future use within 692D100 actuators. Refer to Table 3 herein for disposition of Ball 

Detent Matched Set, P/N 692C181-1.
767/777 Aircraft 

SERVICE BULLETIN

692D100-13 Actuator

Original Issue –SEPTEMBER 13, 2012 692D100-52-4

Revision 3: AUGUST 14, 2014 Page 5

Use or disclosure of data contained on this page is subject to the restriction on the first page of this document

2. Material Information: 

A. Material – Price and Availability 

Table 2 lists the minimum parts required to perform this service bulletin. 

Eaton Aerospace LLC shall perform this action (materials and labor) for $19,700 per unit 

(US Dollars). This price is effective until December 31st, 2014. 

Operators should contact Eaton Aerospace LLC, Fuel and Motion Control Systems 

Division to purchase parts listed in Table 2 below or to obtain possible special pricing 

based on quantities. Please contact: 

Eaton Aerospace LLC, Fuel and Motion Control Systems Division 

3675 Patterson Ave SE, 

Grand Rapids, MI 49512 

Table 2. Required Parts for Service Bulletin Performance 

ITEM 

NO. 

*IPL FIG 1 

ITEM #

QUANTITY PART NO. PART DESCRIPTION PRICE 

US DOLLARS 

1 -- 1 692D100-52-4 Service Bulletin ----- 

2 2-23 1 692C130-1 Ball Detent, Matched Set $5991.54 each 

3 1-17 3 692C114-1 Gear, Planetary $464.73 each 

4 1-2 1 692C193-1 Plate, Identification $165.38 each 

5 1-45 1 999803-02 Plate, Compliance $25.00 each 

6 2-8 1 SA13309-1 Bearing, Ball $ 209.80 each 

7 2-17 1 SA13308-1 Bearing, Ball $ 240.26 each 

NOTE: Replacement of additional parts may be required as determined by the CHECK and 

TESTING AND FAULT ISOLATION sections of CMM 52-34-02, Revision 13 or later. 

B. Industry Support Information – Not Applicable 

C. Material Necessary for Each Component – Refer to Table 2 above. 

D. Material Necessary for Each Spare – Not Applicable 
767/777 Aircraft 

SERVICE BULLETIN

692D100-13 Actuator

Original Issue –SEPTEMBER 13, 2012 692D100-52-4

Revision 3: AUGUST 14, 2014 Page 6

Use or disclosure of data contained on this page is subject to the restriction on the first page of this document

E. Parts Disposition 

Table 3 lists the disposition of the parts that are removed during the performance of this 

Service Bulletin. 

Table 3. Parts Disposition/Information 

ITEM 

NUMBER 

NEW 

PART 

NUMBER 

*IPL 

FIG 1 

ITEM # 

QTY KEYWORD 

OLD PART 

NUMBER 

INSTRUCTIONS/ 

DISPOSITION 

1 692D100-52-4 -- 1 Bulletin, Service --- --- 

2 692C130-1 

(see Note 1) 

2-23 1 Ball Detent, 

Matched Set 

692C181-1 DESTROY 

REMOVED ITEM 

3 692C114-1 1-17 3 Gear, Planetary 692C114-1 DESTROY 

REMOVED ITEM 

4 692C193-1 1-2 1 Plate, Identification 692C193-1 DISCARD OLD 

AS REQUIRED 

5 999803-02 1-45 1 Plate, Compliance N/A N/A 

6 SA13309-1 2-8 1 Bearing, Ball SA13309-1 DESTROY 

REMOVED ITEM 

7 SA13308-1 2-17 1 Bearing, Ball SA13308-1 DESTROY 

REMOVED ITEM 

NOTE 1: P/N 692C130-1 Ball Detent Matched set contains: 1-each Input Shaft, P/N 692C117-1, 

1-each Brake Support Plate, P/N 692C119-1, 1-each Input Sun Gear, P/N 692C116-1, 

6-each Ball, P/N SA13571-1 and 1-each Washer, P/N 692B128-1. 

F. Consumable Materials 

Table 4 lists common consumable materials that are recommended for accomplishment 

of this Service Bulletin. Suitable equivalents may be substituted for items listed. These 

consumable materials are not furnished by Eaton Aerospace. 

Table 4. Consumable Materials 

DESCRIPTION SPECIFICATION SOURCE (CAGE) 

Alcohol, Isopropyl TT-I-735A Commercially Available 

Lockwire MS20995C20 Commercially Available 

Primer BMS 10-11, Type I, Class A, 

Grade B 

Commercially Available 

Sealant MMM-A-1617,Type III Commercially Available 

Insulating Compound MIL-I-46058C, Type UR Commercially Available 

Grease, Aircraft MIL-PRF-23827, Type II Commercially Available 

Paint, Enamel, Exterior (As 

Needed) 

BMS 10-60, Type I, Class B, 

Grade D – White 702 

AKZO Nobel Materials Division 

Waukegan, IL 

CAGE 91342 

Gloves, Blue Nitrile --- Commercially Available 

Sealant BMS5-26, Type I Commercially Available 

Paint Marker, Markal Pro-Line, 

Microtip 

-- Commercially Available 
767/777 Aircraft 

SERVICE BULLETIN

692D100-13 Actuator

Original Issue –SEPTEMBER 13, 2012 692D100-52-4

Revision 3: AUGUST 14, 2014 Page 7

Use or disclosure of data contained on this page is subject to the restriction on the first page of this document

G. Special Tooling – Price and Availability – As listed in CMM 52-34-02 

3. Accomplishment Instructions 

A. Inspection – Perform visual inspection of unit and proceed as outlined in Figure 1 below. 

Recommended Inspection Process Flow 

Figure 1
767/777 Aircraft 

SERVICE BULLETIN

692D100-13 Actuator

Original Issue –SEPTEMBER 13, 2012 692D100-52-4

Revision 3: AUGUST 14, 2014 Page 8

Use or disclosure of data contained on this page is subject to the restriction on the first page of this document

B. Accomplishment - For 692D100-13 Actuators Identified in Table 1 herein which do NOT 

already have a compliance plate. - Unless stated otherwise, item numbers mentioned 

herein refer to IPL Figure 1 of CMM 52-34-02. 

1) On the actuator housing, in an area with intact paint and within 2.00 inches (50.80 mm) 

of the ID plate (preferably above the ID plate and PMA label), clean the area using 

isopropyl alcohol (Table 4). Allow to air dry completely.

Compliance Plate, P/N 999803-02 

Figure 2 

NOTE: As shown in Figure 2, Compliance Plate, P/N 999803-02 (Table 3) shall have 

data pre-stamped by Eaton Aerospace before shipping to operators. 

2) Remove adhesive backing from compliance plate. Do not contaminate adhesive 

surface. 

3) Press the plate firmly to the actuator with fingers in the cleaned and dry area as 

described in paragraph 3. B. 1) above. Refer to Figure 3 for view of recommended 

location on actuator housing. Remove any trapped air bubbles beneath plate. 
767/777 Aircraft 

SERVICE BULLETIN

692D100-13 Actuator

Original Issue –SEPTEMBER 13, 2012 692D100-52-4 

 Revision 3: AUGUST 14, 2014 Page 9

Use or disclosure of data contained on this page is subject to the restriction on the first page of this document

Recommended Location for Applying Compliance Plate 

Figure 3 

4) All edges shall be firmly adhered. Overcoat the compliance plate including edges plus 

0.120 inch min (3.040 mm) beyond edge of plate with insulating compound MIL-I-46058C, 

Type UR. Allow to air dry 30 minutes minimum. 

5) Upon completion of Section 3. B., perform modification step defined in Section 3. C. 

NOTE: Actuator shown 

removed from aircraft for clarity 

purposes 
767/777 Aircraft 

SERVICE BULLETIN

692D100-13 Actuator

Original Issue –SEPTEMBER 13, 2012 692D100-52-4

Revision 3: AUGUST 14, 2014 Page 10

Use or disclosure of data contained on this page is subject to the restriction on the first page of this document

C. Accomplishment - For 692D100-13 Actuators Identified in Table 1 herein which already 

have a compliance plate - Unless stated otherwise, item numbers mentioned herein refer to 

IPL Figure 1 of CMM 52-34-02. 

1) On the actuator housing, clean the ID plate using isopropyl alcohol (Table 4). Allow to 

air dry completely.

2) Using a micro tip paint pen (Table 4), completely obscure the existing part number dash 

“13” and existing SCD number dash “3”. See Figure 4 below for location.

3) Using a micro tip paint pen (Table 4), and immediately to the right of the obscured dash 

number, enter/write “15”.

4) Using a micro tip paint pen (Table 4), and immediately to the right of the obscured SCD 

dash number, enter/write “5”.

5) If the paint pen writing is not legible, remove the marking using a clean rag slightly 

moistened with isopropyl alcohol (Table 4), and allow to dry completely. Re-mark ID 

plate as indicated in steps 3.C.2-4 above until a satisfactory result is achieved. Allow 

paint pen markings to dry a minimum of one (1) minute. 

6) Overcoat all of the paint pen markings plus 0.120 inch min (3.040 mm) beyond markings 

with insulating compound MIL-I-46058C, Type UR (Table 4). Allow insulating compound 

to air dry 30 minutes minimum. 

Re-Mark Identification Plate - Representative View Shown 

Figure 4
767/777 Aircraft 

SERVICE BULLETIN

692D100-13 Actuator

Original Issue –SEPTEMBER 13, 2012 692D100-52-4 

 Revision 3: AUGUST 14, 2014 Page 11

Use or disclosure of data contained on this page is subject to the restriction on the first page of this document

D. Accomplishment - For 692D100-13 Actuators Not Identified in Table 1 herein 

1) Disassemble to Remove No-Back Assembly-– (Unless stated otherwise, item numbers 

mentioned herein refer to IPL Figure 1 of CMM 52-34-02). 

a) To remove no-back assembly (5), first remove the nuts (6), washers (7) and bolts 

(8), and then carefully break sealant fillet and lift the assembly from main housing 

(42). Set no-back assembly aside. 

b) Remove thrust bearing race (12), bearing (13), thrust bearing race (12) and the 

input carrier (item 18) from main housing (42). 

c) Remove shim(s) (9), (10) and (11) from no-back assembly (5). 

NOTE: Shims (9, 10 and 11) may be affixed to the thrust bearing race (12) or bearing 

(13). Separation from these components may be required. 

d) Remove three pins (14), six thrust washers (15) and three planetary gears (17) 

from input carrier (18). Press out bearing (16) from each planetary gear (17). Set 

bearings (16) aside for reuse but destroy the three planetary gears (17). 

NOTE: Various items removed during disassembly should be destroyed to prevent 

inadvertent reuse at a later time. (Ref. Table 3). 

(2) With No-Back Assembly (5) removed from actuator, refer to IPL Figure 2 of 

CMM 52-34-02 and continue the disassembly of no-back assembly as follows: 

(a) Remove support plate (2) by removing nuts (3), washers (4) and screws (5). 

(b) Press bearing (8) out of the support plate (2) and remove shims (6). Destroy 

bearing (8). 

(c) Remove shims (9), bearing (10), ring (11), shims (12) and Belleville spring (13). 

CAUTION: THE INPUT SHAFT (24), BRAKE SUPPORT PLATE (26), INPUT 

SUN GEAR (28), BALLS (25) AND WASHER (27) COMPRISE A MATCHED 

SET (P/N 692C181-1). THESE PARTS MUST BE MAINTAINED AS AN 

ASSEMBLY. 

(d) Remove and destroy ball detent set items (items 24 through 28). 

(e) Remove bearing (17) from input housing (14). Destroy bearing (17). 

NOTE: Various items removed during disassembly shall be destroyed to prevent 

inadvertent reuse at a later time. (Ref. Table 3). 

NOTE: Gloves (Table 4) should be worn when handling items 20 through 22 to prevent 

contamination to bonded friction surfaces. 

(f) Remove items (20 through 22) and set aside for reuse.
767/777 Aircraft 

SERVICE BULLETIN

692D100-13 Actuator

Original Issue –SEPTEMBER 13, 2012 692D100-52-4

Revision 3: AUGUST 14, 2014 Page 12

Use or disclosure of data contained on this page is subject to the restriction on the first page of this document

(g) Carefully remove existing ID plate (2, IPL Figure 1) from actuator housing and set 

aside for data transfer. The ID plate will be replaced with new ID plate. 

(3) Clean all removed parts per the CLEANING section of CMM 52-34-02. 

NOTE: Inspection of items (20 through 22) should be done per CHECK section of 

CMM 52-34-02 to ensure the unit passes requirements of TESTING AND 

FAULT ISOLATION section of CMM 52-34-02 (Revision 13 or later). 

(4) Re-Assemble Actuator (Unless otherwise specified, refer to IPL Figure 1 of 

CMM 52-34-02) 

(a) Apply light application of MIL-PRF-23827, Type II grease (Table 4) to three 

bearings (16). 

(b) Press bearing (16) (removed in step 3. D. 1) d) above) into new planetary gear 

(17) (as listed in Table 3 herein). Reinstall remaining two bearings (16) into the 

new planetary gears (17). Refer to Figure 5 below for installation view. 

(c) Install thrust washers (15) and planetary gears (17) into the input carrier (18). 

(d) Correctly align and install input planetary pins (14) into the input carrier (18). 

NOTE: The step on input planetary pins (14) should face the no-back assembly (5) 

after installation. Refer to Figure 5 herein for view. 

(e) Apply approximately 2 grams of MIL-PRF-23827, Type II grease (Table 4) to the 

gear teeth of each planetary gear (17). 

(f) Install assembled carrier (18) into housing (42). 

Input Planetary Pin (14) Undercut Orientation 

Figure 5 
767/777 Aircraft 

SERVICE BULLETIN

692D100-13 Actuator

Original Issue –SEPTEMBER 13, 2012 692D100-52-4

Revision 3: AUGUST 14, 2014 Page 13

Use or disclosure of data contained on this page is subject to the restriction on the first page of this document

(5) Assemble new ball detent set - Unless stated otherwise, item numbers mentioned 

below refer to IPL Figure 2 of CMM 52-34-02. These items are listed in Table 3 NOTE 1 

herein as follows: 

(a) Remove any excess grease from balls (25) and pockets of matched set. 

(b) Reassemble the input shaft (24) and input sun gear (28) into the brake support 

plate (26). Make sure to align the single alignment mark between the input shaft 

(24) and the brake support plate (26). Also, make sure to align the double 

alignment marks between the input sun gear (28) and the brake support plate (26). 

Refer to Figure 6 for view of assembly. 

Verify Alignment Marks on Input Shaft (24)/Brake Support Plate (26) 

And Input Sun Gear (28)/Brake Support Plate (26) 

Figure 6 

(c) Install shims (15) into input housing (14). 

(d) Apply primer (BMS10-11, Type 1, Class A, Grade B, Table 4) to the new bearing 

(17) surface of input shaft (24). Wipe off excess primer. 

(e) Press new bearing (17) into input housing (14). 

(f) Reinstall items 20 through 22 into input housing (14). Refer to Table 3 NOTE 1.
767/777 Aircraft 

SERVICE BULLETIN

692D100-13 Actuator

Original Issue –SEPTEMBER 13, 2012 692D100-52-4

Revision 3: AUGUST 14, 2014 Page 14

Use or disclosure of data contained on this page is subject to the restriction on the first page of this document

(g) Apply BMS10-11, Type I, Class A, Grade B primer (Table 4) to the OD of the input 

shaft (24). Refer to Figure 7. 

(h) Install new detent matched set P/N 692C130-1, (23) into the input housing (14). 

Refer to Figure 7. 

(i) Install Belleville spring (13), shims (12), ring (11), bearing (10) and shims (9). 

Applying Primer to OD of Input Shaft (24) 

Figure 7 
767/777 Aircraft 

SERVICE BULLETIN

692D100-13 Actuator

Original Issue –SEPTEMBER 13, 2012 692D100-52-4

Revision 3: AUGUST 14, 2014 Page 15

Use or disclosure of data contained on this page is subject to the restriction on the first page of this document

NOTE: Bearing (10) should be installed with the formed edges of bearing race facing 

down against the ring (11). 

NOTE: Shims (12 and 9) value less than 0.010 inch (0.250 mm) cannot be in contact 

with bearing (10). 

CAUTION: DO NOT ALLOW PRIMER TO CONTACT THE INPUT SHAFT (24) 

SURFACE. 

(j) Install shims (6) into support plate (2). 

(k) Apply BMS10-11, Type I, Class A, Grade B primer (Table 4) to OD of new bearing 

(8) within support plate (2) and install bearing (8). 

(l) Install support plate (2) onto input housing (14) and install four screws (5). Torque 

screws 34-36 in-lbs. (3.84 – 4.06 Nm). 

(m) Using a feeler gage, measure and note the gap (endplay) between bearing (8) and 

support plate (2), and between bearing (17) and input housing (14). Adjust shims 

(6) in plate (2), and adjust shims (15) into input housing (14) as necessary to limit 

the total end clearance to within 0.008 in. to 0.014 in (0.203 to 0.355 mm). 

(n) Verify running torque of no-back assembly. Torque shall be 26-33 in-lbs (2.94 – 

3.73 Nm). 

(o) Apply sealant (MMM-A-1617 Type III, Table 4) to the groove of OD of support plate 

(2) and input housing (14) and around screws (5). Refer to Figure 8 herein for view 

of area to be sealed. 

(p) Allow MINIMUM of one (1) hour at ambient room temperature for sealant to cure. 

(6) Determine the shim stack required for unit endplay by measuring from the main housing 

(42) flange to the top of the thrust washer (12), bearing (13) and thrust washer (12) 

stackup on the input carrier (18). Record measurement. 

(7) Measure from top of the input housing (14, IPL Figure 2) flange to the top of the support 

plate (2, IPL Figure 2) thrust washer (12) surface. Record measurement. 

(8) Subtract measurement noted in step (6) above from measurement noted in step (7) to 

determine required shims (9, 10, 11). 

(9) Install shims (9, 10, 11) on top of the thrust washer (12), bearing (13), thrust washer 

(12) stackup to obtain 0.010 to 0.020 inch (0.250 - 0.510 mm) endplay. 

NOTE: Unless stated otherwise, items mentioned in steps 3. D. (10) through 3. D. (16) 

refer to IPL Figure 1 of CMM 52-34-02. 

(10) Install assembled no-back assembly (5) into main housing (42). 

(11) Install nuts (6), washers (7) and bolts (8). Torque bolts (8) 63 to 67 in-lbs. (7.11 – 7.56 

Nm). 
767/777 Aircraft 

SERVICE BULLETIN

692D100-13 Actuator

Original Issue –SEPTEMBER 13, 2012 692D100-52-4

Revision 3: AUGUST 14, 2014 Page 16

Use or disclosure of data contained on this page is subject to the restriction on the first page of this document

Applying Sealant 

Figure 8 

(12) Perform and satisfactorily complete all tests listed in TESTING AND FAULT 

ISOLATION section of CMM 52-34-02. 

(13) Seal exposed threads using BMS5-26, Type I sealant (Table 4) and also fillet seal 

the joint between main housing (42) and no-back assembly (5) using same 

sealant. 

(14) Install lockwire (Table 4) per MS33540 to the unit hardware noted during 

disassembly. 

(15) Apply primer (Table 4) and paint (Table 4) to touch-up the surface finish on 

actuator as needed.
767/777 Aircraft 

SERVICE BULLETIN

692D100-13 Actuator

Original Issue –SEPTEMBER 13, 2012 692D100-52-4

Revision 3: AUGUST 14, 2014 Page 17

Use or disclosure of data contained on this page is subject to the restriction on the first page of this document

(16) Re-Identification of Actuator 

(a) Preparation/Installation of New Identification Plate (2, IPL Figure 1) -Transfer 

the following information from the old identification plate (2) removed in step 

3. D. (2) (g) above to the new identification plate as shown: 

692D100 –15

UNIT SERIAL NUMBER: XXXXB

MFR DATE MONTH YEAR : MMYY (I.E. 0110, January 2010)

WEIGHT: 22.5 

SCD: S135W132-5

NOTE: Step 1 below MUST be accomplished before attaching the ID plate (2) to 

the actuator housing. 

(1) Impression stamp a “B” suffix immediately following the actuator serial 

number using 0.125 inch (3.175 mm) Gothic character. 

(2) Verify integrity of surface area of actuator housing (42, IPL Figure 1) 

where the new ID plate (2) is to be affixed. If surface area is satisfactory, 

go to step (3) below. If required, re-apply primer (Table 4) and exterior 

paint (Table 4) to area requiring touch-up. Allow paint to dry thoroughly 

(10-12 hours) prior to applying new identification plate. 

(3) Clean the surface area of actuator housing (42, IPL Figure 1) for the new 

identification plate (2) with isopropyl alcohol (Table 4). Allow to air dry. 

(4) Carefully peel the protective film layer from adhesive side of ID plate (2). 

DO NOT contaminate the adhesive surface. 

(5) Position one edge of ID plate (2) to the mounting surface and work the 

remainder down in a progressive motion to the opposite edge. Avoid 

stretching the foil as poor adhesion may result. 

(6) Press the ID plate (2) firmly to the mounting surface with fingertips 

and/or a tongue depressor. All edges must be firmly adhered. 

(7) Overcoat the ID plate including edges plus 0.120 inch min (3.048 mm) 

beyond edge of plate with insulating compound MIL-I-46058C, Type UR 

(Table 4). Allow to air dry 30 minutes minimum.