# Eaton Service Bulletin 692D100-52-4: Revision 3

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- Document: [Eaton Service Bulletin 692D100-52-4](https://openairdocs.org/service-documents/eaton/692d100-52-4.md)
- Title as filed: SB 692D100-52-4 Rev 3
- Pages: 18
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- Page: https://openairdocs.org/service-documents/eaton/692d100-52-4/file/b30ce0efeeff

## Text

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### Page 1

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

### Page 2

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

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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 
2821B 
 
2406B

### Page 4

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 re-
marking 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.)

### Page 5

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.

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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

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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, Identif ication 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

### Page 8 (OCR)

SEATON
767/777 Aircraft
SERVICE BULLETIN
692D100-13 Actuator
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.
Inspection
2  3  4
Is the serial  Does the unit have  Perform modification
number on Table  a compliance  defined in Section 3.B
12  plate?  and continue to step 7
No
5
Perform
modification
defined in Section  Does the identification  Perform
Yes  modification
3.D.  plate identify the unit as  defined in Section
a 692D100-13?
3.C.
Service Bulletin has
been incorporated.
No further action
required.
Recommended Inspection Process Flow
Figure 1
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

### Page 9

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 complianc e 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.

### Page 10

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

### Page 11

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

### Page 12

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.

### Page 13

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

### Page 14

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.

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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

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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 no te 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 uni t 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).

### Page 17

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.

### Page 18

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.

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