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, DA TED JAN. 21, 2013 AND REVI SION 2, DATED AUGUST 01,

2013.

Subject: Revision 3 to SB 692D100-52-4 Date: August 14, 2014



### COMPLIANCE INFORMATION RELA TED 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, date d 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 th is revision to further identify affected units by serial
number. Specific changes to text or graphics ar e 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

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### Page 2
Use or disclosure of data contained on this page is subj ect 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

# 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 subj ect 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 provideinstructions 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 1 st 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 subj ect 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 

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Use or disclosure of data contained on this page is subj ect 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 

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Use or disclosure of data contained on this page is subj ect 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

# 767/777 Aircraft
SERVICE BULLETIN
692D100-13 Actuator

Original Issue –SEPTEMBER 13, 2012 

# 692D100-52-4

Revision 3: AUGUST 14, 2014 

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Use or disclosure of data contained on this page is subj ect 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

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# 692D100-52-4

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Use or disclosure of data contained on this page is subj ect 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.

# 767/777 Aircraft
SERVICE BULLETIN
692D100-13 Actuator

Original Issue –SEPTEMBER 13, 2012 

# 692D100-52-4

Revision 3: AUGUST 14, 2014 

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Use or disclosure of data contained on this page is subj ect 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 

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Use or disclosure of data contained on this page is subj ect 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

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Use or disclosure of data contained on this page is subj ect 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 disa ssembly 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 disa ssembly 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 subj ect 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
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692D100-13 Actuator

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Use or disclosure of data contained on this page is subj ect 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 subj ect 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
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692D100-13 Actuator

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# 692D100-52-4

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Use or disclosure of data contained on this page is subj ect 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).

# 767/777 Aircraft
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Use or disclosure of data contained on this page is subj ect 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
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692D100-13 Actuator

Original Issue –SEPTEMBER 13, 2012 

# 692D100-52-4

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Use or disclosure of data contained on this page is subj ect 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: XXXX 

## B

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.