| |
Inspection of Power Distribution Panels |
| |
a. The CH-47 helicopter is designed with two redundant three-phase 400 hertz AC electrical power distribution systems. Fault protection is provided through magnetic type CBs and generator control units. The two AC systems are normally isolated and operate independently of each other. If one generator goes off-line, the generator contactor relays and bus tie CBs act to interconnect the systems (Number 1 and Number 2 main AC busses), allowing the remaining generator to supply all AC power requirements. DC power is also supplied off each AC system through voltage rectifiers. |
| |
b. Inherent cockpit water intrusion is subjecting the Power Distribution Panel (PDP) main CBs ([i.e. Phase A/B/C Number 1 and Number 2 AC auxiliary (aux) PDP feed CBs (MH-47E installation only) and phase A/B/C Number 1 and Number 2 AC bus tie CBs]) to water entry. Subsequent, moisture/salt water induced corrosion is causing a conductive path buildup between individual CB phase case lower power studs and the metal restraint pin which mechanically secures the 3 case CB gang bar assembly together. If a sufficient conductive path develops, arcing occurs, resulting in a short circuit between phases. |
01 21 141323Z APR 97 PP PP UUUU
FROM
:CDRATCOM ST LOUIS MO//AMSAT-R-X//
TO
:AIG 8881
:AIG 9004
:AIG 8708
:AIG 9042
:AIG 7471
:AIG 12124
:USMILGP BUENOS AIRES AR//ARMY AND AF SEC//
:DEFAIR MATERIAL CANBERRA AS//DAAP-AF//
:CDRUSARDSG CANBERRA AS//AMXIP-AS//
:ARGENTINE AIR ATTACHE FMS WASHINGTON DC
:EGYPT AF FMS CAIRO EG//ED/MA//
:USOMC CAIRO EG//AV//
:ODC ATHENS GR//ODCSA//
:CHJUSMAG SEOUL KOR//MKAR-AV//
:ROK ARMY FMS PUSAN KOR//ALC-LSD-L//
:CDR160TH SOAR FT CAMPBELL KY//AOAV-SI//
:CDRBGAD RICHMOND KY//SIOBG-GC//
:USDAO RABAT MO//AF//
:ODC THE HAGUE NL//AVIATION SAFETY//
:RNLAF MATERIAL
:RNLAF OPERATIONS
:CDRUSASAC NEW CUMBERLAND PA//AMSAC-SALO-UK//
:CHUSAS RIYADH SA//ASAV//
:SAO SINGAPORE SN//AVIATION SAFETY//
:ODC MADRID SP//ASM//
:SPAIN ARMY FMS MADRID SP
:AIT TAIPEI TW
:TAIWAN ARMY FMS TAIPEI TW
:CJUSMAG THAI BANGKOK TH//MAGTAR-FS//
:ROYAL THAI ARMY FMS BANGKOK TH//BANGSUE DEPOT//
:ROYAL THAI AF FMS BANGKOK TH//DUSIT ORDANCE DEPOT//
:CDRUSARDSG LONDON UK//AMXSN-UK-SE//
:ODC LONDON UK
INFO
:FAA SOUTHWEST RGN HQ FORT WORTH TX//ASW-100//
:CDRAMC ALEXANDRIA VA//AMCMR/AMCCS/AMCSM-WAA//
XMT
:USDAO DHAKA BG
:USDAO RANGOON BM
:USCINCPAC REP PHNOM PENH CB
:USDAO COLOMBO CE
:USDAO SUVA FJ
:OMADP JAKARTA ID
:DSA NEW DELHI IN
:AMEMBASSY ANTANANARIVO MA
:AMEMBASSY PORT LOUIS
:SAO KUALA LUMPUR MY
:AMEMBASSY KATHMANDU NP//POL-MIL//
ACCT
:
TEXT
:UNCLAS
SUBJECT: AVIATION SAFETY ACTION MESSAGE (ASAM), (MAINTENANCE
MANDATORY), RCS CSGLD-1860(R1), ALL CH-47D, MH-47D, AND MH-47E
AIRCRAFT ONE TIME RECURRING INSPECTION OF POWER DISTRUBUTION
FEEDER WIRING FOR FRAYING/CHAFFING AND ARCING/BURNING; CERTAIN
POWER DISTRIBUTION PANEL (PDP) CIRCUIT BREAKERS (CBS) FOR WATER
INTRUSION INDUCED CORROSION OR ARCING AND BURNING, AND
INSTALLATION OF CIRCUIT BREAKER (CB) COVERS/SEALS (CH-47-97-ASAM-
07)(TB 1-1520-240-20-95).
NOTE - THIS IS AN AVIATION SAFETY ACTION MESSAGE (ASAM) ISSUED
PER AR 95-3, CHAPTER 5 REVISION VIA MESSAGE, HQ AVSCOM, AMSAV-
XSOF, 181900Z SEP 90, SUBJECT: CHANGE TO AR 95-3, CHAPTER 5,
SAFETY OF FLIGHT MESSAGES. THIS ASAM HAS NOT BEEN TRANSMITTED TO
UNITS SUBORDINATE TO ADDRESSEES. ADDRESSEES SHOULD IMMEDIATELY
RETRANSMIT THIS MESSAGE TO ALL SUBORDINATE UNITS, ACTIVITIES OR
ELEMENTS AFFECTED OR CONCERNED. THE RETRANSMITTAL SHALL
REFERENCE THIS MESSAGE. ACTION ADDRESSES WILL IMMEDIATELY VERIFY
THIS TRANSMISSION TO COMMANDER, ATCOM, ATTN: AMSAT-R-X (SOF
COMPLIANCE OFFICER).
1. PRIORITY CLASSIFICATION -
A. AIRCRAFT IN USE - UPON RECEIPT OF THIS ASAM THE
CONDITION STATUS SYMBOL OF THE CITED AIRCRAFT WILL BE CHANGED TO
A RED HORIZONTAL DASH //-//. THE RED HORIZONTAL DASH //-// MAY
BE CLEARED WHEN THE INSPECTION OF PARA 8 BELOW IS COMPLETED. THE
AFFECTED AIRCRAFT SHALL BE INSPECTED AS SOON AS PRACTICAL BUT NO
LATER THAN THE TASK/INSPECTION SUSPENSE DATE. FAILURE TO COMPLY
WITH THE REQUIREMENTS OF THIS ASAM WITHIN THE TIME FRAME REQUIRED
WILL CAUSE THE STATUS SYMBOL TO BE UPGRADED TO A RED //X//.
B. AIRCRAFT IN DEPOT MAINTENANCE - INSPECT AND CORRECT
PRIOR TO ISSUE. AIRCRAFT SHALL NOT BE ISSUED UNTIL COMPLIANCE
WITH THIS ASAM HAS BEEN COMPLETED.
C. AIRCRAFT UNDERGOING MAINTENANCE - SAME AS PARA 1A.
D. AIRCRAFT IN TRANSIT - SAME AS PARA 1A.
E. MAINTENANCE TRAINERS (CATEGORY A, B) - SAME AS PARA 1A.
F. COMPONENT/PARTS IN STOCK AT ALL LEVELS (DEPOT AND
OTHERS) INCLUDING WAR RESERVES - N/A.
G. COMPONENTS/PARTS IN WORK - N/A.
2. TASK/INSPECTION SUSPENSE DATE - WITHIN 10 HOURS/14 DAYS.
3. REPORTING COMPLIANCE SUSPENSE DATE - NO LATER THAN 2 MAY
1997 PER PARA 14A OF THIS MESSAGE.
4. SUMMARY OF PROBLEM -
A. THE CH-47 HELICOPTER IS DESIGNED WITH TWO REDUNDANT
THREE-PHASE 400 HERTZ AC ELECTRICAL POWER DISTRIBUTION SYSTEMS.
FAULT PROTECTION IS PROVIDED THROUGH MAGNETIC TYPE CBS AND
GENERATOR CONTROL UNITS. THE TWO AC SYSTEMS ARE NORMALLY
ISOLATED AND OPERATE INDEPENDENTLY OF EACH OTHER. IF ONE
GENERATOR GOES OFF-LINE, THE GENERATOR CONTACTOR RELAYS AND BUS
TIE CBS ACTS TO INTERCONNECT THE SYSTEMS (NUMBER 1 AND NUMBER 2 MAIN
AC BUSSES), ALLOWING THE REMAINING GENERATOR TO SUPPLY ALL AC POWER
REQUIREMENTS. DC POWER IS ALSO SUPPLIED OFF EACH AC SYSTEM
THROUGH VOLTAGE RECTIFIERS.
B. INHERENT COCKPIT WATER INTRUSION IS SUBJECTING THE POWER
DISTRIBUTION PANEL (PDP) MAIN CBS ([I.E. PHASE A/B/C NUMBER 1 AND
NUMBER 2 AC AUXILIARY (AUX) PDP FEED CBS (MH-47E INSTALLATION ONLY)
AND PHASE A/B/C NUMBER 1 AND NUMBER 2 AC BUS TIE CBS]) TO WATER
ENTRY. SUBSEQUENT, MOISTURE/SALT WATER INDUCED CORROSION IS CAUSING A
CONDUCTIVE PATH BUILDUP BETWEEN INDIVIDUAL CB PHASE CASE LOWER POWER
STUDS AND THE METAL RESTRAINT PIN WHICH MECHANICALLY SECURES THE 3
CASE CB GANG BAR ASSEMBLY TOGETHER. IF A SUFFICIENT CONDUCTIVE PATH
DEVELOPS, ARCING OCCURS, RESULTING IN A SHORT CIRCUIT BETWEEN
PHASES.
NOTE
A PHASE SHORT BETWEEN POWER DISTRUBUTION FEEDER WIRING MAY
ALSO RESULT IN THE PROBLEM AS DESCRIBED BELOW.
ONCE A PHASE SHORT OCCURS, THE APPROPRIATE GENERATOR CONTROL UNIT
(GCU) FUNCTIONS NORMALLY TO TAKE THE FAULTED SIDE GENERATOR OFF-
LINE. WITH THE GENERATOR CONTACTOR RELAY SWITCH OPEN (RELAY DE-
ENERGIZED) AND BUS TIE CLOSED (GANG BAR ON POSITION), SYSTEM
DESIGN ALLOWS THE NUMBER 1 AND NUMBER 2 AC DISTRIBUTION SYSTEMS
TO BECOME INTERCONNECTED AND THE NON-FAULTED SIDE GENERATOR TO
POWER ALL AC DISTRIBUTION BUSES. WITH THE FAULT STILL PRESENT,
THE EXPECTED DESIGN RESULT IS AN AUTOMATIC BUS TIE OVER-CURRENT
TRIP CONDITION. BY DESIGN, ONCE THE BUS TIE CB TRIPS THE INITIAL
FAULT WOULD AGAIN BE ISOLATED, ALLOWING THE NON-FAULTED SIDE
GENERATOR TO MAINTAIN POWER TO THE NON-FAULTED SIDE BUSES.
HOWEVER, IT IS SUSPECTED THAT MOISTURE/SALT WATER
INDUCED CORROSION MAY CAUSE AN ELECTRICAL SYSTEM ANOMALY WHEREIN
THE BUS TIE CB MAY OR MAY NOT FUNCTION TO TRIP PRIOR TO THE GCU
REACTION. THE END RESULT IS BOTH GENERATORS GOING BOTH OFF-LINE
WITH ONLY 28V DC ESSENTIAL BUS AVAILABILITY. THE RAMIFICATIONS
OF THE FOREGOING CAN BE CATASTROPHIC, ESPECIALLY DURING IMC
FLIGHT CONDITIONS.
C. OUR INVESTIGATION OF THIS COCKPIT WATER INTRUSION AND
ELECTRICAL SYSTEM ANOMALY PROBLEM HAS REVEALED THAT IT IS COMMON
TO CH-47D AND MH-47D/E AIRCRAFT.
D. FOR MANPOWER/DOWNTIME AND FUNDING IMPACTS, SEE PARA 12
BELOW.
E. THE PURPOSE OF THIS ASAM IS AS FOLLOWS:
(1) INSPECT POWER DISTRUBUTION FEEDER WIRING FOR EVIDENCE
OF FRAYING/CHAFFING AND ARCING/BURNING, AND TO REPLACE ANY THAT
SHOW SIGNS OF SUCH.
(2) INSPECT PDP BUS TIE AND AUX FEED MAIN CBS
FOR EVIDENCE OF WATER/MOISTURE, ARCING/BURNING AND CORROSION/SALT
DEPOSITS, AND TO REPLACEMENT OF ANY THAT SHOW SIGNS OF SUCH.
(3) ESTABLISHES A RECURRING 200 HOUR PHASE INSPECTION
REQUIREMENT FOR ALL CH-47 AIRCRAFT.
(4) EMPHASIZE COVERING COCKPIT ELECTRICAL COMPONENTS SUCH
AS P.D.P.S, AND INSTRUMENT PANELS/CONSOLE, DURING AIRCRAFT
WASHING AND CLEANING.
(5) TO IMMEDIATELY REQUISITION, AND INSTALL (AS SOON AS
THEY BECOME AVAILABLE), PDP AUX FEED (MH-47E ONLY) AND BUS TIE CB
PLASTIC DUST BOOTS (WATER PROOF COVERS WITH SEALING
CAPABILITY). OVER THE PDP AUX FEED AND BUS TIE CBS. THE CB DUST
BOOT INSTALLATION SHALL BE PERFORMED SUBSEQUENT TO CB INSPECTION
LISTED IN PARA 9B.
F. THIS THESE ASAM PROCEDURES SIMPLE MODIFICATION WILL
SIGNIFICANTLY REDUCE THE POSSIBILITY OF COCKPIT WATER INTRUSION
PREVE INDUCING PDP BUS TIE AND AUX FEED MAIN CB CORROSION AND THE
SUBSEQUENT SHORTING OF THE AC ELECTRICAL SYSTEM.
5. END ITEMS TO BE INSPECTED - ALL CH-47D, MH-47D, AND MH-47E
AIRCRAFT.
6. ASSEMBLY COMPONENTS TO BE INSPECTED - N/A.
7. PARTS TO BE INSPECTED -
A. CH-47D AND MH-47D AIRCRAFT:
NOMENCLATURE PART NO. NSN
NO. 1 AC BUS TIE AM3-Z370-2 5925-01-130-3573
CIRCUIT BREAKER
NO. 2 AC BUS TIE
CIRCUIT BREAKER AM3-Z370-2 5925-01-130-3573
B. MH-47E AIRCRAFT:
NOMENCLATURE PART NO. NSN
NO. 1 AC AUX PDP AM3C3A45-1 NONE
FEED CIRCUIT BREAKER
NO. 1 AC BUS TIE AM3-Z370-2 5925-01-130-3573
CIRCUIT BREAKER
NO. 2 AC AUX PDP AM3C3A45-1 NONE
FEED CIRCUIT BREAKER
NO. 2 AC BUS TIE AM3-Z370-2 5925-01-130-3573
CIRCUIT BREAKER
8. INSPECTION PROCEDURES -
A. PREPARE THE AIRCRAFT FOR SAFE GROUND MAINTENANCE.
B. BATTERY DISCONNECTED [REFER TO CHAPTER 1, TM 55-1520-240-
23-1 (CH-47D AND MH-47D) OR TM 1-1520-252-23-1 (MH-47E)].
C. ELECTRICAL POWER OFF.
D. HYDRAULIC POWER OFF.
E. OPEN NO. 1 AND NO. 2 PDP AND REMOVE THE NO. 1 AND
NO. 2 AC BUS TIE CBS AND THE NO. 1 AND NO. 2 AUX PDP FEED CBS
[REFER TO TM 55-1520-240-23-7, TASK 9-10, (CH-47D AND MH-47D) OR
TM 1-1520-252-23-9, TASK 9-14, (MH-47E)].
NOTE
PROCEDURE IS THE SAME TO GAIN ACCESS TO CBS IN THE NO. 1 OR
NO. 2 POWER DISTRIBUTION PANELS (PDPS) IN ALL CH/MH-47
AIRCRAFT.
F. (CH-47D AND MH-47D) VISUALLY INSPECT THE NO. 1 AND NO. 2
AC BUS TIE CBS (REFER TO TM 55-1520-240-23P-2, FIGURE 307, INDEX
26, AND FIGURE 309, INDEX 31) FOR PRESENCE OF WATER/MOISTURE,
ARCING/BURNING, AND CB TERMINAL STUDS/HARDWARE FOR EVIDENCE OF
CORROSION/SALT. PAY PARTICULAR ATTENTION TO LOWER LOCK WASHER
(WASHER CONTACTING CB CASE) AREA FOR ANY SIGNS OF CORROSION/SALT
DEPOSITS.
NOTE
CORROSION MAY FORM ON UNDER SIDE OF CB TERMINAL STUD LOWER
LOCK WASHER OR IN ADJACENT AREA OF CB CASE SEAM.
G. (MH-47E) VISUALLY INSPECT THE NO. 1 AND NO. 2 AC BUS TIE
CBS (REFER TO TM 1-1520-252-23P-3, FIGURE 9-7, INDEX 35, AND
FIGURE 9-8, INDEX 43) AND THE NO. 1 AND NO. 2 AUX PDP FEED CBS
(REFER TO TM 1-1520-252-23P-3, FIGURE 9-7, INDEX 44, AND FIGURE 9-
8, INDEX 43) FOR EVIDENCE OF WATER/MOISTURE, ARCING/BURNING, AND
CB TERMINAL STUDS/HARDWARE FOR EVIDENCE OF CORROSION/SALT. PAY
PARTICULAR ATTENTION TO LOWER LOCK WASHER (WASHER CONTACTING CB
BODY) AREA FOR ANY SIGNS OF CORROSION/SALT DEPOSITS.
NOTE
CORROSION MAY FORM ON UNDER SIDE OF CB TERMINAL STUD LOWER
LOCK WASHER OR IN ADJACENT AREA OF CB CASE SEAM.
H. REPLACE ANY CB SHOWING SIGNS OF WATER/MOISTURE INTRUSION,
ARCING/BURNING, OR CORROSION/SALT DEPOSITS. REPLACE THE CB IN
ACCORDANCE WITH TM 55-1520-240-23-7, TASKS 9-10 AND 9-11 (CH-47D
AND MH-47D) OR
TM 1-1520-252-23-9, TASKS 9-14 AND 9-15 (MH-47E) WITHIN
TASK/INSPECTION SUSPENSE DATE.
I. VISUALLY INSPECT THE NO. 1 AND NO. 2 AC POWER
DISTRUBUTION (FEEDER) WIRES FOR EVIDENCE OF FRAYING/CHAFFING OR
ARCING/BURNING.
J. REPLACE ANY POWER DISTRUBUTION/FEEDER WIRE SHOWING SIGNS
OF ABOVE (REFER TO WITH TM 55-1500-323-24, SECTION 14).
K. IF NO CB SHOWS SIGNS OF WATER/MOISTURE, ARCING/BURNING,
OR CORROSION/SALT DEPOSITS, RECORD AND REPORT COMPLIANCE WITH THE
INSPECTION PORTION OF THIS ASAM IN ACCORDANCE WITH PARA 14 BELOW.
L. FOR CORRECTIVE ACTION FOR ALL CH/MH-47D/E AIRCRAFT TO
REDUCE THE POSSIBILITY OF WATER INTRUSION CORRODING PDP MAIN CB
TERMINAL STUDS AND THE SUBSEQUENT SHORTING OF THE AC ELECTRICAL
SYSTEM, REFER PARA 9 BELOW.
9. CORRECTION PROCEDURES -
A. IMMEDIATELY REQUISITION DUST BOOT PARTS KITS SPECIFIED IN
PARA 10A BELOW. REQUISITION TWO (2) KITS FOR CH-47D AND MH-47D
AIRCRAFT, AND FOUR (4) KITS FOR MH-47E AIRCRAFT.
NOTE
IT MAY TAKE 6-8 MONTHS FOR DLA TO PROCURE SUFFICIENT PARTS
KITS TO SUPPORT THIS REQUIREMENT. ENSURE YOUR REQUISITIONS
ARE SUBMITTED IMMEDIATELY THROUGH NORMAL SUPPLY CHANNELS, AND
CONTINUE TO MONITOR STATUS UNTIL PARTS KITS ARE RECEIVED.
B. UPON RECEIPT OF THE DUST BOOT PARTS KITS SPECIFIED
IN PARA 10A BELOW, PERFORM THE INSTALL THE PARTS KITS AS
FOLLOWINGS. MAINTENANCE PROCEDURES.
(1) PREPARE THE AIRCRAFT FOR SAFE GROUND MAINTENANCE.
(2) BATTERY DISCONNECTED [REFER TO CHAPTER 1, TM 55-1520-
240-23-1 (CH-47D AND MH-47D) OR TM 1-1520-252-23-1 (MH-47E)].
(3) ELECTRICAL POWER OFF.
(4) HYDRAULIC POWER OFF.
(5) OPEN NO. 1 AND NO. 2 PDP AND REMOVE THE NO. 1 AND
NO. 2 AC BUS TIE CBS AND THE NO. 1 AND NO. 2 AUX PDP FEED CBS
[REFER TO TM 55-1520-240-23-7, TASK 9-10, (CH-47D AND MH-47D) OR
TM 1-1520-252-23-9, TASK 9-14, (MH-47E)].
NOTE
PROCEDURE IS THE SAME TO GAIN ACCESS TO CBS IN THE NO. 1 OR
NO. 2 PDPS IN ALL CH/MH-47 AIRCRAFT.
(6) (CH-47D AND MH-47D) VISUALLY INSPECT THE NO. 1 AND
NO. 2 AC BUS TIE CBS (REFER TO TM 55-1520-240-23P-2, FIGURE 307,
INDEX 26, AND FIGURE 309, INDEX 31) FOR EVIDENCE OF
WATER/MOISTURE, ARCING/BURNING, AND CB TERMINAL STUDS/HARDWARE
FOR EVIDENCE OF CORROSION/SALT. PAY PARTICULAR ATTENTION TO
LOWER LOCK WASHER (WASHER CONTACTING CB CASE) AREA FOR ANY SIGNS
OF CORROSION/SALT DEPOSITS.
NOTE
CORROSION MAY FORM ON UNDER SIDE OF CB TERMINAL STUD LOWER
LOCK WASHER OR IN ADJACENT AREA OF CB CASE SEAM.
(7) (MH-47E) VISUALLY INSPECT THE NO. 1 AND NO. 2 AC
BUS TIE CBS (REFER TO TM 1-1520-252-23P-3, FIGURE 9-7, INDEX 35,
AND FIGURE 9-8, INDEX 43) AND THE NO. 1 AND NO. 2 AUX PDP FEED
CBS (REFER TO TM 1-1520-252-23P-3, FIGURE 9-7, INDEX 44, AND
FIGURE 9-8, INDEX 43) FOR PRESENCE OF WATER/MOISTURE,
ARCING/BURNING, AND CB TERMINAL STUDS/HARDWARE FOR EVIDENCE OF
CORROSION/SALT. PAY PARTICULAR ATTENTION TO LOWER LOCK WASHER
(WASHER CONTACTING CB BODY) AREA FOR ANY SIGNS OF CORROSION/SALT
DEPOSITS.
NOTE
CORROSION MAY FORM ON UNDER SIDE OF CB TERMINAL STUD LOWER
LOCK WASHER OR IN ADJACENT AREA OF CB BODY SEAM.
(8) IMMEDIATELY REPLACE ANY CB SHOWING SIGNS OF
WATER/MOISTURE INTRUSION, ARCING/BURNING, OR CORROSION/SALT
DEPOSITS. REPLACE THE CB IN ACCORDANCE WITH TM 55-1520-240-23-7,
TASKS 9-10 AND 9-11 (CH-47D AND MH-47D) OR TM 1-1520-252-23-9,
TASKS 9-14 AND 9-15 (MH-47E).
(9) VISUALLY INSPECT THE NO. 1 AND NO. 2 AC POWER
DISTRUBUTION (FEEDER) WIRES FOR EVIDENCE OF FRAYING/CHAFFING AND
ARCING/BURNING.
(10) REPLACE ANY POWER DISTRUBUTION/FEEDER WIRE SHOWING
SIGNS OF ABOVE (REFER TO WITH TM 55-1500-323-24, SECTION 14).
(1) PREPARE AIRCRAFT FOR SAFE GROUND MAINTENANCE.
DISCONNECT BATTERY AND TURN OFF ELECTRICAL AND HYDRAULIC POWER.
(2) REMOVE PDP CBS LISTED IN PARA 6 ABOVE. REFER TO
TM 55-1520-240-23, TASK 9-10 (CH-47D AND MH-47D) OR
TM 1-1520-252-23, TASK 9-14 (MH-47E).
(113) POSITION THE PLASTIC BOOT FROM THE PARTS KIT
THROUGH THE PDP INSIDE CB OPENING, ENSURING THAT THE MOLDED WORD
"ON" ON THE PLASTIC BOOT IS IN PROPER ALIGNMENT WITH THE PRINTED
WORDS "ON" ON THE CB. INSTALL THE STEEL FRAME WITH FLANGED SIDE
FACING FWD, ENSURING THAT PROPER CONTACT IS MADE WITH THE PLASTIC
BOOT AND PDP INSIDE COVER.
NOTE
TO ATTAIN THE PROPER SEAL, ENSURE THAT THE FLANGE IS NOT
INSTALLED UPSIDE DOWN AND THAT THE PLASTIC BOOT CONTACTS THE
FLANGED SIDE OF THE STEEL FRAME SYMMETRICALLY.
(412) INSTALL THE CB THROUGH THE BACK SIDE OF THE PDP
OPENING AND DRAW FIRMLY INTO PLACE USING THE SIX(6) SCREWS WITH O-
RINGS PROVIDED IN THE PARTS KIT.
(513) COMPLETE CB INSTALLATION IN ACCORDANCE WITH
TM 55-1520-240-23-7, TASK 9-11 (CH-47D AND MH-47D) OR
TM 1-1520-252-23-9, TASK 9-15.
C. REPORT COMPLIANCE WITH THE ABOVE IN ACCORDANCE WITH PARA
14B BELOW.
10. SUPPLY/PARTS AND DISPOSITION -
A. PARTS REQUIRED -
(1) ITEMS CITED IN PARA 7 ABOVE MAY BE REQUIRED TO
COMPLY WITH THE ABOVE PARA 8 AND PARA 9 ABOVE INSPECTION PORTION
OF THIS ASAM.
(2) THE FOLLOWING ITEMS WILL BE REQUIRED TO COMPLY WITH
THE PARA 9 ABOVE CORRECTIVE ACTION PORTION OF THIS ASAM -
NOMENCLATURE PART NUMBER NSN
PARTS KIT, DUST BOOT HE1050 2530-00-755-6196
B. REQUISITIONING INSTRUCTIONS - REQUISITION REPLACEMENT
PARTS THROUGH NORMAL SUPPLY CHANNELS USING NORMAL SUPPLY
PROCEDURES. ALL REQUISITIONS SHALL USE PROJECT CODE XDE PER
THIS MESSAGE.
NOTE
PROJECT CODE XDE IS REQUIRED TO TRACK AND ESTABLISH A DATA BASE
OF STOCK FUND EXPENDITURES INCURRED BY THE FIELD AS A RESULT OF
SOF/ASAM ACTIONS.
C. BULK AND CONSUMABLE MATERIALS - N/A.
D. DISPOSITION - DISPOSE OF REMOVED PARTS IAW NORMAL SUPPLY
PROCEDURES. A QDR IS NOT REQUIRED.
E. DISPOSITION OF HAZARDOUS MATERIAL - N/A.
11. SPECIAL TOOLS, JIGS AND FIXTURES REQUIRED - N/A.
12. APPLICATION -
A. CATEGORY OF MAINTENANCE - AVUM. AIRCRAFT DOWNTIME WILL
BE CHARGED TO AVUM.
B. ESTIMATED TIME REQUIRED -
(1) TOTAL OF 3 MAN-HOURS USING 1 PERSON.
(2) TOTAL OF 3 HOURS DOWNTIME FOR ONE END ITEM.
C. ESTIMATED COST IMPACT OF STOCK FUND ITEMS TO THE FIELD -
NOUN PART NSN QTY UNIT TOTAL
NUMBER COST COST
PARTS HE1050 2530-00-755-6196 2 $17.10 $34.20
KIT (CH/MH- *
47D)
PARTS HE1050 2530-00-755-6196 4 $17.10 $68.40
KIT (MH- * *
47E)
D. TB/MWOS TO BE APPLIED PRIOR TO OR CONCURRENTLY WITH THIS
INSPECTION - N/A.
E. PUBLICATIONS WHICH REQUIRE CHANGE AS A RESULT OF THIS
INSPECTION -
(1) TM 55-1520-240-23-9, TASKS 9-10 AND 9-11.
(2) TM 1-1520-252-23-9, TASKS 9-14 AND 9-15.
(3) TM 55-1520-240-23P-2, FIGURES 307 AND 309.
(4) TM 1-1520-252-23P-2, FIGURES 9-7 AND 9-8.
(5) TM 55-1520-240-PM.
(6) TM 55-1520-252-PM.
13. REFERENCES -
A. TM 55-1520-240-23-9.
B. TM 55-1520-240-23P-2.
C. TM 1-1520-252-23-9.
D. TM 1-1520-252-23P-3.
E. TM 55-1520-240-PM.
F. TM 1-1520-252-PM.
G. TM 55-1500-323-24.
14. RECORDING AND REPORTING REQUIREMENTS -
A. REPORTING COMPLIANCE SUSPENSE DATE (AIRCRAFT) - UPON
ENTERING REQUIREMENTS OF THIS ASAM ON DA FORM 2408-13-1 ON ALL
SUBJECT MDS AIRCRAFT, FORWARD A PRIORITY MESSAGE, DATA FAX OR
E-MAIL TO COMMANDER, ATCOM, ATTN: AMSAT-R-X (SOF COMPLIANCE
OFFICER), PER AR 95-3. DATA FAX NUMBER IS DSN 693-2064 OR
COMMERCIAL (314) 263-2064. E-MAIL ADDRESS IS "AMSATRXS (AT SIGN)
EMH4.STL.ARMY.MIL". THE REPORT WILL CITE THIS ASAM NUMBER, DATE
OF ENTRY IN DA FORM 2408-13-1, THE AIRCRAFT MISSION DESIGN SERIES
AND SERIAL NUMBERS OF AIRCRAFT IN NUMERICAL ORDER.
B. TASK/INSPECTION REPORTING SUSPENSE DATE (AIRCRAFT) -
UNITS WILL FORWARD A PRIORITY MESSAGE OR DATA FAX TO: COMMANDER,
ATCOM, ATTN: AMCPM-CH-L. DATA FAX NUMBER IS DSN 693-1485 OR
COMMERCIAL 314/263-1485. THE REPORT WILL CITE THIS ASAM NUMBER,
DATE OF INSPECTION, AIRCRAFT SERIAL NUMBER, AIRCRAFT HOURS, AND
RESULTS OF THE INSPECTION. INSPECTION AND REPORTS WILL BE
COMPLETED NO LATER THAN 5 WORKING DAYS AFTER TASK/INSPECTION
SUSPENSE DATE.
C. REPORTING COMPLIANCE SUSPENSE DATE (SPARES) - N/A.
D. TASK/INSPECTION REPORTING SUSPENSE DATE (SPARES) - N/A.
E. THE FOLLOWING FORMS ARE APPLICABLE AND ARE TO BE
COMPLETED IN ACCORDANCE WITH DA PAM 738-751, 15 JUN 92 -
(1) DA FORM 2408-13, AIRCRAFT STATUS INFORMATION
RECORD.
(2) DA FORM 2408-13-1, AIRCRAFT INSPECTION AND
MAINTENANCE RECORD.
(3) DA FORM 2408-15, HISTORICAL RECORD FOR AIRCRAFT.
(4) DA FORM 2408-18, EQUIPMENT INSPECTION LIST (CARRY
THE INSPECTION ON THE DA FORM 2408-18 UNTIL IT IS INCORPORATED
INTO THE PHASE TM). ULLS-A USERS SHOULD USE AN 800 NUMBER FOR
THE INSPECTION UNTIL IT IS INCORPORATED INTO THE PHASE TM.
15. WEIGHT AND BALANCE - N/A.
16. POINTS OF CONTACT -
A. TECHNICAL POINT OF CONTACT FOR THIS MESSAGE IS
MR. LARRY WIESCHHAUS, AMSAT-R-ECC, DSN 693-6678 OR COMMERCIAL
314/263-6678, AND FAX IS DSN 693-1485 OR COMMERCIAL 314/263-1485.
B. LOGISTICAL POINT OF CONTACT FOR THIS MESSAGE IS MR. MIKE
MELLIERE, AMCPM-CH-L, DSN 693-1901 OR COMMERCIAL 314/263-1901 AND
FAX IS DSN 693-1485 OR COMMERCIAL 314/263-1485.
C. WHOLESALE MATERIEL POINT OF CONTACT (SPARES) FOR THIS
MESSAGE IS MR. HAL BARNES, AMSAT-I-SACA, DSN 693-6031 OR
COMMERCIAL 314/263-6031 AND FAX IS DSN 693-6022 OR 314/263-6022.
D. FORMS AND RECORDS POINT OF CONTACT FOR THIS MESSAGE IS
MS. ANN WALDECK, AMSAT-I-MDM, DSN 490-2318 OR COMMERCIAL 314/260-
2318.
E. SAFETY POINT OF CONTACT FOR THIS MESSAGE IS MR. JIM
WILKINS, AMSAT-R-X, DSN 693-2258 OR COMMERCIAL 314/263-2258.
F. FOREIGN MILITARY SALES (FMS) RECIPIENTS REQUIRING
CLARIFICATION OF ACTION ADVISED BY THIS ASAM SHOULD CONTACT CW5
JAY NANCE/MR. RON VAN REES, AMSAT-D-S, DSN 693-7844/3216 OR
COMMERCIAL 314/263-7844/3216.
G. AFTER HOURS CONTACT ATCOM COMMAND OPERATIONS CENTER
(COC), DSN 693-2066/7 OR COMMERCIAL 314/263-2066/7.