flolht/obsidian_lht
1
0
Fork 0
Code Issues Pull Requests Actions Packages Projects Releases Wiki Activity

initial upload

Browse Source
This commit is contained in:
flo
2025-07-01 12:01:28 +02:00
commit 27c8fd9561
260 changed files with 99376 additions and 0 deletions
Download Patch File Download Diff File Expand all files Collapse all files

4
AMM/00 - REV 139.md Normal file
View File

@ -0,0 +1,4 @@
## High-Speed Tape Inspection Interval
Note: Unless otherwise specified in the CDL item or the relevant AMM task, a visual inspection of the high-speed tape must be made at a regular interval that must not exceed 3 calendar days.

9
AMM/11 - Placards.md Normal file
View File

@ -0,0 +1,9 @@
---
created: 2023-01-04T13:34:46+01:00
updated: 2023-01-04T13:37:22+01:00
---
[EO 356329 - A320 Technical Markings](EO/EO%20356329)
[[DLHA3202TM.pdf]]
[[DLHA3202TM_Partslist.pdf]] Partslist
[[A320_NEO_DLH12_NEW_LIVERY_v1.pdf]]

4
AMM/20 - Standarts.md Normal file
View File

@ -0,0 +1,4 @@
### Sicherungsdraht
- 14QFB1 - MS20995N32 - Inconel 371 C
- 14QFC1 - MS20995C32 - CRES

29
AMM/23 - Communication.md Normal file
View File

@ -0,0 +1,29 @@
---
created: 2023-01-14T17:24:15+01:00
updated: 2025-04-25T02:57
---
## Allgemein
| Task | Ref |
| ----------------- | ----------- |
| Static Discharger | 23-61-41-04 |
## -40
### Horn
| Description | PN |
| ----------- | --------------- |
| horn | D0003004300000 |
| contact | EN3155-016M1616 |
| connection | NSA936830-16 |
## CIDS
| Task | Ref |
| ------------------------- | ------------------ |
| Interface & Power-up Test | 23-73-00-740-005-B |

39
AMM/24 - Electrical Power.md Normal file
View File

@ -0,0 +1,39 @@
### 24-92 Bondings / Inspections
| Item | Ref |
|------|-----|
| Bondings Flightcontrols | 24-92-00-210-024-A |
SUBTASK 24-92-00-220-063-B
C. Inspection of the Elevator Bonding Leads
(1) During the inspection, if you cannot replace the bonding leads that are broken or damaged, the bonding lead installations that follow are satisfactory:
(a) Bonding lead installed near the elevator tip:
- If less than 25 percent of its strands are damaged.
(b) And for the other bonding leads installed on the elevator:
- If only one bonding lead is broken or has more than 25 percent of its strands damaged and the other bonding leads have less than 25 percen of their strands damaged.
(2) Replace all the remaining broken or damaged bonding leads in less than 24 months or 7500 flight hours or 5000 flight cycles (the one that occurs first).
## Battery Protect C/Bs
| PANEL | LOC | DESIGNATION | FIN |
| ----------- | --- | ------------------------------- | ----- |
| 2PB1(BAT-1) | | | |
| 105VU | A01 | FLT CTL/ELAC1/STBY SPLY | 16CE1 |
| 105VU | B01 | FLT CTL/SEC1/STBY SPLY | 22CE |
| 105VU | C01 | ELEC/CSM/G /EV AUTO/SPLY | 7XE |
| 105VU | D01 | ELEC/HOT BUS/701PP SPLY | 5PB1 |
| 105VU | E01 | ELEC/HOT BUS/701PP SPLY | 12PB1 |
| 105VU | F01 | ELEC/BAT REF/BCL1 | 9PB1 |
| 105VU | J01 | NAV/STBY/INST/BAT | 23FN |
| 2PB2(BAT-2) | | | |
| 105VU | A02 | FLIGHT CONTROLS/ELAC2/STBY SPLY | 16CE2 |
| 105VU | C02 | ADIRS/ADIRU1/28VDC | 6FP1 |
| 105VU | D02 | ELEC/HOT BUS/702PP SPLY | 5PB2 |
| 105VU | E02 | ELEC/HOT BUS/702PP SPLY | 12PB2 |
| 105VU | F02 | ELEC/BAT REF/BCL2 | 9PB2 |
| 105VU | G02 | ELEC/STAT INV/CNTOR/CTL | 14XB |
| 106VU | B04 | CSM/G /EV/MAN/SPLY | 6XE |

105
AMM/25 - Cabin.md Normal file
View File

@ -0,0 +1,105 @@
---
created: 2023-01-14T17:24:28+01:00
updated: 2025-05-14T14:14
---
### 25-10 Cockpit Seats
| Item | Ref |
|----------------|----------|
| Safety Harness | 25-11-63 |
### 25-20 Passenger Cabin
| Item | Ref |
|------------------------|---------------------------------|
| Center Ceiling Stowage | 25-24-01 -- EB-SR 00140536/004 |
| Repl Curtain | 25-26-41-04 |
| Item | Ref |
|---------------------|---------------|
| Heated Floor Panels | \[\[EO 342978\]\] |
### 25-30 Galleys
| Item | PN | Ref. |
|----------------|-----------------|--------------------|
| Aft Max Galley | 601539-101 | CMM 25-36-62 REV 8 |
| Oven New | 8303-06-0000-01 | CMM 25-37-39 REV 4 |
### 25-40 Toilets
#### NEW F/G
Dispenser Toilet Paper Spindle Assy
A081112-507 25-40-17-26/25 CMM
### 25-50 Cargo Loading System
#### PDU Roller
ALT AMM: 25-50-00-200-018-A
NEU AMM: 50-20-03-200-804-A01 / EO367283
| Version | Durchmesser | Breite | Ausbrüche |
|---------|-------------|--------|-----------|
| alt | 40,8 | 48.8 | 2 |
| neu | 39 | 25 | 3 |
### 25-60 Emergency Equipment
| | |
| --------- | ------------ |
| Life Vest | 25-66-52-04 |
| EMK/FAC | SPM 25-00-05 |
#### Lifevest expiration date
![[life_vest_exp_date.png]]
### 25-80
| Insulation Blankets | |
|----------------------------|--------------------|
| repair insulation blankets | 25-80-00-350-001-A |
## CRAS
### Tape Repair
Die folgenden Hinweise ersetzen nicht das Originaldokument (CRAS 00146367) und dienen als
ergänzende Hinweise. Wichtige Änderungen und Hinweise zum CRAS 00146367 Revision 5:
a) Eine Reparatur gemäß CRAS 00146367 REV 5 ist für 180 Tage gültig.
b) Für Tape-repairs ist ausschließlich das in 1. Material aufgeführte Tape zu verwenden.
Tabelle 1; Material für eine Reparatur mittels Tape.
Manufacturer: 81205
| Item | Description | P/N | Remarks |
|-------------------------------------------------------------------------------------------|----------------------------------|-------------------|----------------------------------------------------------------------|
| 1 | Pressure sensitive adhesive tape | PATCO D9100-1INCH | 33m x 25mm |
| 2 | Pressure sensitive adhesive tape | PATCO D9100-2INCH | 33m x 51mm |
| 3 | Pressure sensitive adhesive tape | PATCO D9100-XINCH | X in suffix denotes tape width in inch. Max width of 4 in is allowed |
c) In Kapitel 2. Accomplishment ist die Durchführung und der zulässige Umfang für das
Reparaturverfahren beschrieben. Die integrierte Tabelle zeigt eine Liste der Defekte, die
mit Tape repariert werden können. Zusätzlich werden bestimmte Bereiche (HIC path
area) von dem Reparaturverfahren ausgeschlossen.
**Tabelle 2; Zulässige Bereiche für die Anwendung der CRAS.**
a) Cracks in Mirrors
b) Cracks in small seat fairings
c) Coverage of sharp edges of broken parts if they are still fixed well without tape
d) Um das CRAS anzuwenden sind für die Beschädigungen folgende Limits definiert:
Tabelle 3; Limits für die Anwendung des Reparaturverfahrens.
| | Spiegel | Sitze |
|----------------------------|------------------|-------------------|
| Gesamtfläche | 1 sqft / 900 cm² | 36 sqin / 253 cm² |
| Fläche Beschädigung | 9 sqin | |
| Mindestabstand Reparaturen | 12 in | |
Sollte die vorgefundene Beschädigung nicht abgedeckt sein ist das TCC unter
069/69643711 zu kontaktieren.

0
AMM/26 - Fire Detection.md Normal file
View File

21
AMM/27 - Flight Control.md Normal file
View File

@ -0,0 +1,21 @@
### Elevator
| Doc | Ref | Description |
| --- | ------------ | -------------- |
| CMM | 55-21-15/036 | Elevator Assy |
| EO | 333322/01 | Elev PN -> A/C |
| AMM | 27-34- | Elevator SCU |
### Flap/Slat PPUs Position
**Flaps:** AMM 27-50-00-860-801-A PB201
**Slats:** AMM 27-80-00-860-801-A PB201
- retracted position:
APPU to FPPU: +- 0.9 deg.
APPU to APPU: +- 0.7 deg.
- extended position:
APPU to FPPU: +- 1.3 deg.
APPU to APPU: +- 0.7 deg.

15
AMM/28 - Fuel.md Normal file
View File

@ -0,0 +1,15 @@
---
created: 2023-07-16T06:15:05+02:00
updated: 2023-07-16T07:17:51+02:00
---
## -42 Capacitance Values
| Grid | Fin | LRU | Dry | Tolerance | Wet Max |
|:---- |:----- |:----------- |:------ |:--------- |:------- |
| A03 | 21QT1 | L/H Probe 1 | 64.516 | ± 0.62 | 135.45 |
| B03 | 92QT1 | L/H Probe 2 | 63.122 | ± 0.60 | 132.62 |
| | | | | | |
| | | | | | |
| | | | | | |
| | | | | | |
| | | | | | |

7
AMM/31 - Indication & Recording.md Normal file
View File

@ -0,0 +1,7 @@
---
created: 2023-01-13T07:28:21+01:00
updated: 2023-01-14T17:13:46+01:00
---
AIDS Passwort DMU: SFIMP

39
AMM/32 - Landing Gear.md Normal file
View File

@ -0,0 +1,39 @@
---
created: 2024-11-18T04:01
updated: 2025-05-02T07:27
---
### -41 WHEELS
| Item | Reference | Notes |
| ---------- | --------- | ------------------------- |
| Main Wheel | 32-41-11 | 220/110 lbft 300/150 lbft |
| Nose Wheel | 32-41-12 | 160/80 lbft |
```ad-info
[[SL 2019-32-004 Radial Tire Sidewall Undulations.pdf]]
```
### -42 BRAKE
Table 1 (Ref. MS-Task 32422701-01)
| BWI Length | FC |
| ---------- | --- |
| 3.5 - 3.9 | 70 |
| 3.0 - 3.4 | 60 |
| 2.5 - 2.9 | 50 |
| 2.0 - 2.4 | 40 |
| 1.5 - 1.9 | 30 |
| 1.1 - 1.4 | 20 |
```ad-note
FOR BWI LENGTH < 1.0 MM BRAKE CHANGE REQUIRED. BUT MAY BE DEFERRED FOR
MAX. 10 FC BASED ON 0.1 MM = 1 FC.
E.G. BWI LENGTH 0.6 MM = 6 FC.
```
```ad-note
| Brake 1 | Brake 2 | Brake3 | Brake4 |
| ------- | ------- | ------ | ------ |
| 2643GM | 2641GM | 2644GM | 2642GM |
```

33
AMM/33 - Lights.md Normal file
View File

@ -0,0 +1,33 @@
---
created: 2024-02-16T09:53:53+01:00
updated: 2025-04-04T22:57
---
``` ad-note
Access Code CAP Test: 3351
```
### Cabin
| Task | Ref |
| -------------- | ----------- |
| Light Unit | 33-21-11-04 |
| Handrail Light | 33-21-21-04 |
| Reading Light | |
### Service
| Task | Ref |
| - | - |
| Service Areas | 33-31-11 |
| Air Cond Area | 33-32-00 |
| Cargo Tubes | 33-34-11 |
| Loading | 33-34-12 |
### Cabin Emergency
| Task | Ref |
| --------- | ------------------ |
| Ops Check | 33-51-00-710-001-A |

8
AMM/35 - Oxygen.md Normal file
View File

@ -0,0 +1,8 @@
---
created: 2024-10-18T03:17
updated: 2024-10-18T03:17
---
Portable Bottle AMM 35-32-42
Refilling SPM 35-00-08
Portable Oxygen Bottle MEL C 35-30-01B

36
AMM/36 - Pneumatic.md Normal file
View File

@ -0,0 +1,36 @@
---
created: 2023-01-04T13:08:36+01:00
updated: 2024-02-16T09:53:54+01:00
---
| Task | Ref |
|------|-----|
| Bleed Check - Ops Test Bleed Air System | 36-11-00-710-003-A |
#### Bleed Check
##### CFM
| N1 % | Druck PSI | Temp °C |
|------|-----------|---------|
| Idle | 20-39 | 150-200 |
| 35-40 | 36 ± 4 | 200 +10 -30 |
| 65 | 44 ± 4 | 200 +10 -40 |
##### V2500
| N1 % | Druck PSI | Temp °C |
|------|-----------|---------|
| Idle | 20-39 | 150-200 |
| 35-40 | 36 ± 4 | 200 +10 -30 |
| 75 | 44 ± 4 | 200 +10 -40 |
##### PW1100
| N1 % | Druck PSI | Temp °C |
|------|-----------|---------|
| Idle | 20-48 | 100-205 |
| 35-40 | 50 ± 2 | 200 ± 25 |
| 80 | 50 ± 2 | 200 ± 25 |
### BMC Current Status

4
AMM/52 - Doors.md Normal file
View File

@ -0,0 +1,4 @@
Repair 52-13-18-08
Fwd Door Seal 52-11-18-300-001-A
Aft Door Seals 52-13-18-300-001-A
Temp Repair High Speed Tape 52-11-18-300-802–A

6
AMM/53 - Fuselage.md Normal file
View File

@ -0,0 +1,6 @@
---
created: 2024-09-06T16:20
updated: 2024-09-06T18:55
---
[[SRM/53 - Fuselage|SRM - 53 - Fuselage]]

3
AMM/57 - Wings.md Normal file
View File

@ -0,0 +1,3 @@
Bushing Repair of Bolt Hole of Tank Panels: SRM 57-21-11-300-009
NOTE: When refitting the panel after repair you must use bolts with a grip length 3.2 mm (0.126 in) longer than the standard bolts.

48
AMM/71 - Engine.md Normal file
View File

@ -0,0 +1,48 @@
---
created: 2023-01-04T14:01:02+01:00
updated: 2024-11-08T21:43
---
Preservation Tag Form-ID: 31809
Missing Part List: 31780
Ident-Tag: 31794
## Preservation
Desiccant Bags (500g per Bag) PN: "VA 16"
| | | | | |
| ------------- | ------------------ | ----------------- | ------------- | --------- |
| | **FWD (Fan Aera)** | **AFT (Exhaust)** | **Gesamt** | **Limit** |
| **PW1100G** | 12,5Kg (25ea) | 12,5Kg (25ea) | 25Kg (50ea) | 40% |
| **V2500** | 22,5KG (45ea) | 22,5KG (45ea) | 45Kg (90ea) | 40% |
| **CFM56-5A** | 15Kg (30ea) | 15Kg (30ea) | 30Kg (60ea) | 20% |
| **CFM56-5B** | 15Kg (30ea) | 15Kg (30ea) | 30Kg (60ea) | 70% |
| **CFM56-5C** | 8Kg (16ea) | 8Kg (16ea) | 16Kg (32ea) | |
| **CF6-80** | | | | |
| **Trent-900** | 65Kg (130ea) | 65Kg (130ea) | 130Kg (260ea) | |
| **XWB** | 65Kg (130ea) | 65Kg (130ea) | 130Kg (260ea) | |
## CFM56
Preservation:
| Preservation | 72-00-00-03 |
| ------------ | ------------------ |
| -365 | 72-00-00-600-003-A |
| -30 | 72-00-00-600-001-A |
| -90 | 72-00-00-600-002-A |
## V2500
Preservation:
## PW1100
| | AMM |
| --------------------------------------- | ---------------- |
| POWER PLANT SYSTEM MAINTENANCE | 71-00-00-700-806 |
| ENGINE OPERATION LIMITS AND GUIDELINES | 71-00-00-910-803 |
| OPERATE THE ENGINE AFTER SURGE OR STALL | 71-00-00-860-819 |

2
AMM/71 - Run Up.md Normal file
View File

@ -0,0 +1,2 @@
ATA Codes Noise Control Sheet
![[ATA Code Liste Run-Up.jpg]]

59
AMM/72 - Fan.md Normal file
View File

@ -0,0 +1,59 @@
---
created: 2023-07-16T05:22:22+02:00
updated: 2025-04-20T05:18
---
# CFM56-5A
# PW1100
| Task | Ref |
| --------------------------------------- | ---------------- |
| Visual Insp Fan Blade Polyurethane Coat | 71-11-03-220-805 |
# CFM 56-5B
### Fan Blade Inspection
#### Leading Edge Tip Curl
There is not limit on the quantity of blades damaged when the tip curl does not extend more than dimension X1=0.5 IN. (13 MM) across the blade tip and not more than dimension X=0.5 IN. (13 MM), along the leading edge. Maximum deflection from original contour is dimension Y=0.25 IN. (6.35 MM).
A maximum of 6 blades can have tip curl up to dimension X1=1.3 IN. (33 MM) across the blade tip and dimension X=2 IN. (51 MM) along the leading edge with maximum deflection from original contour dimension Y=0.6 IN. (15 MM). Not more than 3 blades to these increased limits can be adjacent.
In all cases, deflection tip angle must not be more than 60 deg (60 deg) 60 degrees from original airfoil. Replace pair of blades if not in the limits Ref. AMM TASK 72-21-00-300-028
No continued in-service extension is permitted.
See sheet 2 of Ref. Fig. Fan Rotor Blades - Local Distortions
#### Trailing Edge Tip Curl
There is not limit on the quantity of blades impacted when the tip curl does not extend more than dimension Z1 =0.5IN. (13 MM) across the blade tip and not more than dimension Z =0.5 IN. (13 MM) with maximum deflection from original contour dimension Y1=0.25 IN. (6.35 MM).
A maximum of 5 blades can have tip curl up to dimension Z1=1 IN. (25.4 MM) across the blade tip and up to dimension Z=1 IN. (25.4MM) along the trailing edge with maximum deflection from original contour dimension Y1=0.3 IN. (7.62 MM).
No more than 3 blades to these increased limits can be adjacent. Replace pair of blades if not in the limits Ref. AMM TASK 72-21-00-300-028.
No continued in-service extension is permitted.
See sheet 2 of Ref. Fig. Fan Rotor Blades - Local Distortions
#### Shingled midspan shrouds
**NOTE:** Shingled means that the midspan shrouds are still overlapped.
Not serviceable.
Refer to over-serviceable-limit extensions Ref. AMM TASK 72-00-00-200-025.
![[Pasted image 20230716052112.png]]
![[Pasted image 20230716052432.png]]
![[Pasted image 20230716052519.png]]
![[Pasted image 20230716052549.png]]
![[Pasted image 20230716052642.png]]

41
AMM/73 - Engine Fuel.md Normal file
View File

@ -0,0 +1,41 @@
---
created: 2023-01-16T08:00:06+01:00
updated: 2024-02-16T09:53:54+01:00
---
## V2500
## SBs
| SB | |
| ------- | ------------------------ |
| 73-1138 | EEC SCN23 Software Stand |
| EEC Softw | EEC PN | Data Plug |
| --------- | ------------------------------------------ | --------- |
| SCN21/AA | 824972-xx-022 or 808050-x-068 | 2A3106 |
| SCN22/AB | 824972-xx-024 or 808050-x-070 or 2A4346 | 2A4378 |
| SCN23/AC | 824972-xx-026 or 808050-x-072 or 2A610 | |
## 73-10
#### Functional Test Fuel Recirculation Cooling
Label Call-up
- 07C/1/245/01 -- Engine 1
- 07C/2/245/10 -- Engine 2
Only bits 28 - 14, ignore 13 - 11
Add SET Bit Values
| 28 | 27 | 26 | 25 | 24 | 23 | 22 | 21 | 20 | 19 | 18 | 17 | 16 | 15 | 14 |
|---- | ---- | ---- | ---- | ---- | --- | --- | --- | --- | --- | --- | --- | --- | --- | --- |
| 16384 | 8192 | 4096 | 2048 | 1024 | 512 | 256 | 128 | 64 | 32 | 16 | 8 | 4 | 2 | 1 |
$$
\text{Valve Position \%} = \frac{\text{added up Value}} {32768} \times 128
$$
Make sure the calculated value is more than 10%
![[73-13-42_Functional Test of the Fuel Recirculation Cooling System with AIDS.pdf]]
______________________________________________________________________________

16
AMM/78 - Exhaust.md Normal file
View File

@ -0,0 +1,16 @@
## 78-30 Trust Reverser
### 78-32 T/R Halves
78-32-30 Cascade
78-32-32 Blocker Door Links
78-32-33 Blocker Door
78-32-34 Sleeve Translating
78-32-41 Thermal Insulation Blankets
### PW1100
Repair Thermal Insulation Blankets 78-32-00-300-802-A
RTV88, RTV9910, SS4004P
Studs CB9461CT3CR8NV
Adhesive EA9321

4
AMM/79 - Oil.md Normal file
View File

@ -0,0 +1,4 @@
## Oil Service
### PW1100
- 79-00-00-03 / 79-00-00-610-801-A

41
AMM/80 - Starting.md Normal file
View File

@ -0,0 +1,41 @@
## PW11
### 80-11-00 Starting
80-11-00-03
Fill Starter with Oil 80-11-00-600-801-A
Fill 473ml - 591ml (16fl.oz. - 20fl.oz.)
80-11-01 Starter
80-11-02 MagPlug
80-11-03 Start Valve
80-11-04 Speed Sensor
### 80-11-49 Starter Duct
#### Inspection GVI LWR STARTER DUCT
Ref. AMM 80-11-00-210-801-A
[TASK](https://airnavx.lht.ham.dlh.de/airnavx/document/635628_SGML_C/toc?itemId=635628_SGML_C_EN80114900080200&itemType=DATAMODULE&wc=actype:A318;actype:A319;actype:A320;actype:A321;customization:DLH;doctype:AMM;tailNumber:N10304)
![[lwr_starter_duct.png]]
| | | |
| --------------------------------------------- | ----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- | -------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |
| Lower duct cracks around the clevis weld seam | If the total crack length is equal to 1.50 in. (38.10 mm) or less. Do an inspection of the crack every 1000 flight cycles to measure the crack length | Permitted (continue in service). |
| | If the total crack length is equal to 2.30 in. (58.42 mm) or less but more than 1.50 in. (38.10 mm), continue in service. Do an inspection of the crack every 500 flight cycles to measure the crack length | Permitted (continue in service). |
| | If the total crack length is equal to 3.00 in. (76.20 mm) or less but more than 2.30 in. (58.42 mm), continue in service. Do an inspection of the crack every 100 flight cycles to measure the crack length | Permitted (continue in service). |
| | If the total crack length is more than 3.00 in. (76.20 mm)<br><br>Ref. Fig. Total Crack Permitted | Not permitted (Remove the duct from service within ten flight cycles) [Ref. AMM TASK 80-11-49-000-802](https://airnavx.lht.ham.dlh.de/airnavx/document/635628_SGML_C/toc?itemId=635628_SGML_C_EN80114900080200&itemType=DATAMODULE&wc=actype:A318;actype:A319;actype:A320;actype:A321;customization:DLH;doctype:AMM;tailNumber:N10304) and Ref. AMM TASK 80-11-49-400-802. |
| | | |
| ------------------ | ----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------ |
| Round bottom dents | Dents in zone 1 that are less than 0.100 in. (2.540 mm) in depth and 3.000 in. (76.200 mm) or more to the nearest edge of a different dent are permitted | Permitted. |
| | Dents in zone 1 that are 0.100 in. (2.540 mm) in depth and less than 0.250 in. (6.350 mm), and more than ten times the depth across, and 3.00 in. (76.200 mm) or more to the nearest edge of a different dent are permitted with a 1000 flight cycle reinspection | Not permitted. Replace the duct Ref. AMM TASK 80-11-49-000-802 and [Ref. AMM TASK 80-11-49-400-802](https://airnavx.lht.ham.dlh.de/airnavx/document/635628_SGML_C/toc?itemId=635628_SGML_C_EN80114940080200&itemType=DATAMODULE&wc=actype:A318;actype:A319;actype:A320;actype:A321;customization:DLH;doctype:AMM;tailNumber:N10304). |
| | Dents in zone 2 that are 0.250 in. (6.350 mm) in depth or less and more than ten times the depth across, and 3.00 in. (76.200 mm) or more to the nearest edge of a different dent are permitted | |
| | Dents in zone 1 and zone 2 that are more than 0.250 in. (6.350 mm) or less than ten times the depth across are not permitted<br><br>Ref. Fig. GVI of the Engine Starting System | |
| Nicks or scratches | Up to 0.025 in. (0.63 mm) depth or less | Permitted. |
| EXAMINE | DAMAGE | DISPOSITION |
| ---------------------------------------- | ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------ | -------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |
| The starter ducts (upper and lower) for: | | |
| Looseness or incorrect assembly | Any amount | Not permitted. Tighten or reassemble as necessary [Ref. AMM TASK 80-11-49-400-802](https://airnavx2.lht.ham.dlh.de/airnavx/document/658069_SGML_C/toc?itemId=658069_SGML_C_EN80114940080200&itemType=DATAMODULE&wc=actype:A318;actype:A319;actype:A320;actype:A321;customization:DLH;doctype:AMM). |
| Round bottom dents | Dents in zone 1 that are less than 0.100 in. (2.540 mm) in depth and 3.000 in. (76.200 mm) or more to the nearest edge of a different dent | Permitted. |
| | Dents in zone 1 that are 0.100 in. (2.540 mm) in depth and less than 0.250 in. (6.350 mm) and more than ten times the depth across, and 3.00 in. (76.200 mm) or more to the nearest edge of a different dent | Permitted with a re-inspection interval of 1000 flight cycles. |
| | Dents in zone 2 that are 0.250 in. (6.350 mm) in depth or less and more than ten times the depth across, and 3.00 in. (76.200 mm) or more to the nearest edge of a different dent | Permitted. |
| | Dents in zone 1 and zone 2 that are more than 0.250 in. (6.350 mm) or less than ten times the depth across<br><br>Ref. Fig. GVI of the Engine Starting System | Not permitted. Replace the duct [Ref. AMM TASK 80-11-49-000-802](https://airnavx2.lht.ham.dlh.de/airnavx/document/658069_SGML_C/toc?itemId=658069_SGML_C_EN80114900080200&itemType=DATAMODULE&wc=actype:A318;actype:A319;actype:A320;actype:A321;customization:DLH;doctype:AMM) and |

37
AMM/AMOS.md Normal file
View File

@ -0,0 +1,37 @@
---
created: 2024-02-16T09:53:54+01:00
updated: 2024-02-16T09:53:54+01:00
---
### 5\.11 Ad Hoc JIC
Mit dieser Funktion werden Taskcards für wiederkehrende Nachkontrollen (O-Items) erstellt. Dies erfolgt bei LHA durch die CAMO ( TCC ) !
#### Erstellung bei LHA
Wir erstellen eine W/O der Ursprungsbeanstandung und stellen diese mittels Transfer zurück. Wir informieren die CAMO mittels Eintrag in den Action-Text (TLB oder AMOS) *„ATT TCC: INITIATE REPETITIV INSPECTION ITEM WITH INTRVAL X” oder“ATT. TCC: INITIATE MMP WITH INTERVAL X”.* Es wird ein TAQ (Query) erstellt in dem dann das TCC auf die Erfordernis eines Ad Hoc JIC aufmerksam gemacht wird. (plus Tel. und/oder CAMO-App). Hier sollten grundlegende Infos über MEL-Ref, Documents, Maßnahme und Timeframe, wenn möglich, enthalten sein.
#### Durchführung
Die Durchführung eines Ad Hoc JIC wird mittels W/P beauftragt. Es handelt sich um eine Taskcard mit der jeweiligen Aufgabe. Die Ausführung wird im W/S durch das Symbol bescheinigt und dann die Taskcard mit (links) geschlossen. Damit wird das Ad Hoc JIC nicht etwa gelöscht, sondern wird mit dem nächsten Termin wieder neu beauftragt. Im Ad Hoc JIC existiert in der Planning View eine Verlinkung zum Ursprünglichen DD.
#### Erledigung
Wird das auslösende DD erledigt (Repair/Change), wird die CAMO automatisch mittels Mail darüber informiert. Zur Sicherheit, kann man dem TCC auch telefonisch und Query darüber informieren, dass ein bestehendes Ad Hoc JIC gelöscht werden kann.
#### Änderungen
Ergeben sich bei der Durchführung eines Ad Hoc JIC ́s Befund-Änderungen: Die zum Ad Hoc JIC zugehörige Transfered W/O ist als Verlinkung in der Planning View sichtbar. Diese W/O muss von der CAMO bzw. der Rolle LMA (BL, PPS) ins W/P eingefügt werden, damit man sie bearbeiten darf. In dieser Ursprungs-W/O wird eine neue Action erstellt, in der die Befundänderung festgehalten wird. Hierbei ist zu beachten, dass eine Befundänderung ggf. Limits und Vorgaben (z.B. auch CRAS) beeinflussen kann und Berücksichtigung finden muss! Hier muss das TCC telefonisch über den neuen Befund informiert werden, um sicherzustellen, das die Ursprungs-W/O weiter als DD verbleiben kann, oder ggf. der Termin angepasst werden muss. Mit dem Wortlaut im Action Text *„ATT TCC. CORRECT RELATED AD HOC JIC“* wird dem TCC zusätzlich kenntlich gemacht, dass das Ad Hoc JIC an sich, für zukünftige Kontrollen, angepasst werden muss. Die Ursprungs-W/O muss nun auch einen neuen „ACTIVE TRANSFER“ erhalten. Der Termin bleibt unverändert, oder wird gem. TCC, CRAS etc. entsprechend angepasst. Hier ist auch wieder das Approval durch die CAMO, mittels Deassign vom W/P erforderlich, wie bei jedem anderen Transfer. Die Taskcard des Ad Hoc JIC wird, wie zuvor beschrieben, bescheinigt.
### 5\.12 Schedule W/O & Briefing Card
Mit der Funktion „Scheduled W/O“  können W/O ́s für einmalige Nachkontrollen oder Instandhaltungs Tätigkeiten erstellt werden. z.B. Fuel Filter Wechsel, nach Tankarbeiten, o.ä.
Mit der Unterfunktion „Briefing Cards“ können Additional Crew Infos generiert werden. Anders, als mit „normalen“ DDs, wird das Due Date hier bis zum letztmöglichen Zeitpunkt ausgereizt, bevor die W/O zur Erledigung geplant wird, bzw. Briefing Cards werden von der CAMO selbst gelöscht.
Beide werden über die APN1418 und den Schalter „New System W/O“ erstellt.  (***Nicht*** über die APN 58 ! ) Im Wizard Step 6 „Work performed“ >>> „NO“ anhaken!
Achtung! Beim Step 7 „Initial Due Information“ wird KEIN Time-Frame eingetragen, sondern das Datum des Endtermins, die Total Aircraft-Hours und/oder die Total Aircraft-Cycles! (nutze hierzu auch die Instant Information durch Links-Klick auf die A/C-Reg im entspr. Wizard-Step) Der zu vergebende Termin ist entweder über den Auftrag angewiesen, oder wird mit der CAMO (TCC ) abgesprochen. Soll sie auf z.B. unbestimmte Zeit laufen, trägt man im Feld Due Date „No Limit“ ein.
Und bitte **keine Classification (M,I,H)** eintragen! Sonst landet es in der HIL nicht unter "Additional Crew Info"!
### Dent & Buckle Chart
APN 786

78
AMM/PW1100 - Fan Blade inspection.md Normal file
View File

@ -0,0 +1,78 @@
Use this procedure to do a visual inspection of the flow path surface of the fan blade polyurethane-coat.
For visual examination of the polyurethane-coated area of the fan-blade root, refer to TASK 72-11-03-210-801-A.
For more information about fan blade examination, refer to TASK 72-11-03-220-803-A.
For more information about the fan rotor assembly, refer to 72-11-00-00
SUBTASK 72-11-03-220-056-A
A. Inspection of the Fan Blade Polyurethane Coat (Flow Path only)
For the inspection limits, refer to Table 1: Visual Inspection of the Fan Blade for Erosion:
``` ad-note
The flow path surface is the part of the blade that you can see when the blade is installed in the engine.
```
``` ad-note
Area D extends 0.5 in. (12.7 mm) from the top of the platform along the blade and 0.5 in. (12.7 mm) from the side of the blade along the platform.
```
``` ad-note
The polyurethane coat is black, the primer is green and the base metal is silver or gray in color.
```
(a) If the missing coat areas do not show the base metal, you can extend the cycle limits by ten more cycles.
(b) Repair the blades that you removed from service because of the missing coat and put them back in service.
![[PW_Coating_01.jpeg]]
![[PW_Coating_02.jpeg]]
![[PW_Coating_03.jpeg]]
| EXAMINE | DAMAGE | DISPOSITION |
| --- | --- | --- |
| The polyurethane coat of the fan blade (1): | | |
| All areas for: | | |
| Missing polyurethane coat without the primer or the base metal shown | Any quantity. | Permitted for local FOD. For erosion Ref. AMM TASK 72-11-03-210-802. |
| Missing polyurethane coat with the primer or the base metal shown | The primer or the base metal you can see less than 1.00 in.2 (645.16 mm2). | See the specified area shown in this procedure. |
| | More than 1.00 in.2 (645.16 mm2) of the primer or the base metal that you can see for each side of the fan blade. | Not permitted. Repair or replace the blade in 750 cycles. The repaired coat must not be more than a total of 10.0 in. (254.00 mm) of the radial height on the full blade set, all quantities axially. See additional requirements for Areas D, E, X and Y. |
| | More than 9.00 in.2 (5806.44 mm2) of the primer or the base metal that you can see for each side of the fan blade. The limits for Areas A thru E above stay applicable. | Not permitted. Repair or replace the blade in 50 cycles. The repaired coat must not be more than a total of 10.0 in. (254.00 mm) of the radial height on the full blade set, all quantities axially. See additional requirements for Area D. |
| | Polyurethane coat that is lifted or has loss of bond. | Not permitted. In ten cycles, cut away the coat that is lifted or has loss of bond by the requirements specified in Para. 4.A.(2) Ref. AMM TASK 72-11-03-320-804. Examine the primer or the base metal that you can see to the limits specified above. |
| ==NOTE==: <br>For the repair procedures of the fan blade polyurethane coat, refer to Para. 4.B. | | |
| Nodules in the coat area (a nodule is a small, rounded, raised lump of coat material that can occur during the manufacturing process) | Nodules in coat must be smooth, continuous and not move with light pressure. | Permitted. |
| Scuff marks or streaks in the coat area (scuff marks and streaks are superficial marks caused by the coated surfaces that rub against each other) | All quantities that do not show primer or base metal. | Permitted. |
| Blend areas on the coat (can occur during the manufacturing process and can have a matte gray finish) | All quantities that do not show primer or base metal. | Permitted. |
| Coat nicks, pits and scratches | All quantities that do not show primer or base metal. | Permitted. |
| Area A | All the primer or the base metal that you can see, 1.00 in.2 (645.16 mm2) or less. | Not permitted. Repair or replace the blade in 2600 cycles. See "Area A adjacent to the blade tip". For areas more than 1.00 in.2 (645.16 mm2), see the "All Areas" section. |
| Area A adjacent to the blade tip | All the primer or the base metal that you can see is not more than 0.0078 in.2 (5.03 mm2) for each side of the blade that is immediately adjacent to the blade tip. The total area does not include the plasma spray tip treatment surface area. It is not necessary for the edges of the plasma coat on the fan blade tip to have polyurethane coat. | Permitted. If the damage is not in the limits, repair or replace the blade in 2600 cycles. |
| Area B | All the primer or the base metal that you can see, 1.00 in.2 (645.16 mm2) or less. | Not permitted. Repair or replace the blade in 1100 cycles. For areas more than 1.00 in.2 (645.16 mm2), see the "All Areas" section. |
| Area C | All the primer or the base metal that you can see, 1.00 in.2 (645.16 mm2) or less. | Not permitted. Repair or replace the blade in 1100 cycles. For areas more than 1.00 in.2 (645.16 mm2), see the "All Areas" section. |
| Area D | All the primer or the base metal that you can see. | Not permitted. If the galvanic isolation is not done or it is not checked, repair or replace the blade in five cycles. If the galvanic isolation is done, repair the blade in 35 cycles. Do a check for the galvanic isolation Ref. AMM TASK 72-11-03-210-803. |
| Area E | All the primer or the base metal that you can see, 1.00 in.2 (645.16 mm2) or less. | Not permitted. If the galvanic isolation is not done or it is not checked, repair or replace the blade in 50 cycles. If the galvanic isolation is done, repair the blade in 1100 cycles. Do a check for the galvanic isolation Ref. AMM TASK 72-11-03-210-803. For areas more than 1.00 in.2 (645.16 mm2) and with the galvanic isolation, see the "All Areas" section. |
| Area E adjacent to the blade tip | All the primer or the base metal that you can see is not more than 0.0031 in.2 (2.00 mm2) for each side of the blade that is immediately adjacent to the blade tip. The total area does not include the plasma spray tip treatment surface area. | Permitted. If not in limits and if the galvanic isolation is not done or it is not checked, repair or replace the blade in 50 cycles. If the galvanic isolation is done, repair the blade in 1100 cycles. Do a check for the galvanic isolation Ref. AMM TASK 72-11-03-210-803. |
| Area E adjacent to the Leading Edge (LE) sheath | Gaps between the polyurethane coat and the LE sheath not more than 0.010 in. (0.254 mm) in width and is not more than the length of the LE sheath. Erosion coat must be firmly attached with no visible primer or base metal. | Permitted. If not in limits and if the galvanic isolation is not done or it is not checked, repair or replace the blade in 50 cycles. If the galvanic isolation is done, repair the blade in 1100 cycles. Do a check for the galvanic isolation Ref. AMM TASK 72-11-03-210-803. |
| Area X of the platform, 2.0 in. (50.8 mm) or less from the ground tab | All the primer or the base metal that you can see. | Not permitted. If the galvanic isolation is not done or it is not checked, repair or replace the blade in 50 cycles. If the galvanic isolation is done, repair the blade in 1100 cycles. Do a check for the galvanic isolation Ref. AMM TASK 72-11-03-210-803. |
| Area Y airfoil area at the Trailing Edge (TE) tip | All the primer or the base metal that you can see. | Permitted. In ten cycles, cut away the coat that is lifted or has loss of bond by the requirements specified in Para. 4.A.(2) Ref. AMM TASK 72-11-03-320-804. |
| Area Z | Coating cracks or gaps. | Not permitted. Remove the blade from service immediately. |
| Gaps or cracks in coating may be a sign of disbond on the fan blade cover. Refer Para. 4.E. for details Ref. AMM TASK 72-11-03-220-802. | | |
| Area Z cover transition area for bubbled coating (air bubble under polyurethane coating). Completely or partially in the cover transition area. An air bubble can have burst showing an area of coating disbond | One bubble total of 0.500 in. (12.700 mm) maximum length parallel to the cover edge. | Not permitted. Remove the blade from service in ten cycles. Every two cycle inspect the blade for signs of disbond as specified in Para. 4.E. Ref. AMM TASK 72-11-03-220-802. Make sure there is no growth of the bubble currently identified or any additional bubbles on the cover perimeter. If the blade is found with any of the above damage, remove the blade from service immediately. |
| | More than one bubble or any bubble beyond 0.500 in. (12.700 mm) length parallel to the cover edge. | Not permitted. Remove the blade from service immediately. |
Table - Table 1: Visual Inspection of the Fan Blade for Erosion
SUBTASK 72-11-03-320-053-A
B. Repair the polyurethane coat of the fan blade (1) as follows:
(1) Damage to the polyurethane coat that does not go through the coat and does not show the primer or the base metal is permitted. No repair is necessary Ref. AMM TASK 72-11-03-210-802.
(2) If the damage shows the primer but does not show the base metal, do an erosion coat touch-up repair of the fan blade assembly with the coating, polyurethane, erosion resistant (Material Ref. P05-154) Ref. AMM TASK 72-11-03-320-804.
(3) If the damage shows the primer or the base metal, do an erosion coat touch-up repair of the fan blade assembly with the epoxy (Material Ref. P05-492) Ref. AMM TASK 72-11-03-320-805.
(4) For the fan blades that must be removed and replaced in Table 1 [Ref. AMM TASK 72-11-03-000-801](https://airnavx.lht.ham.dlh.de/airnavx/document/699554_SGML_C/toc?itemId=699554_SGML_C_EN72110300080100&itemType=DATAMODULE&wc=FSN:109;actype:A318;actype:A319;actype:A320;actype:A321;customization:DLH;doctype:AMM;tailNumber:N8383) and Ref. AMM TASK 72-11-03-400-801.