REVISION NO. 30 Aug 01/05
Pages which have been revised are outlined below, together with the Highlights of the Revision
CH/SE/SU C REASON FOR CHANGE EFFECTIVITY PAGES
CHAPTER 53
L.E.P. 1- 1 REVISED TO REFLECT THIS REVISION INDICATING NEW,REVISED, AND/OR DELETED PAGES
CES
FUSELAGE
LIST OF EFFECTIVE PAGES
_______________________ N, R or D indicates pages which are New, Revised or Deleted respectively Remove and insert the affected pages and complete the Record of Revisions and the Record of Temporary Revisions as necessary
CH/SE/SU C PAGE DATE CH/SE/SU C PAGE DATE CH/SE/SU C PAGE DATE
RECORD OF TEMP. REVISION
L.E.P.
R 1- 1 Aug01/05
T.
of C. 1 Aug01/99
53-OBSV 101 Feb01/98
53-35-00 201 Aug01/99 53-35-00 202 Aug01/99
53-L.E.P. Page Aug 01/05
CES
FUSELAGE
TABLE OF CONTENTS
_________________
SUBJECT_______ CH/SE/SU _ PAGE EFFECTIVITY________ C ____ ___________ FAULT SYMPTOMS 53-OBSV 101 ALL
FAIRINGS 53-35-00 FAULT ISOLATION PROCEDURES 201 ALL Vibration and/or Noise felt in Mid 201 ALL Cabin
53-CONTENTS Page 1 Aug 01/99 R CES
「一一一一一一一一一一一一一一一一一一一一一一一一T一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一T一一一一一一一一一一一一1 CFDS FAULT MESSAGES FAULT WARNINGS/MALFUNCTIONS 十一一一一一一一T一一一一一一一一一一一一一一一一一一一一一一一一T一一一一一一T一1 ISOLATION SOURCE MESSAGE ATA C PROCEDURE
十一一一一一一一一一一一一一一一一一一一一一一一一十一一一一一一一十一一一一一一一一一一一一一一一一一一一一一一一一十一一一一一一十一十一一一一一一一一一一一一1 VIBRATION - Belly 533500 P 201 fairing vibration T 810 801 L一一一一一一一一一一一一一一一一一一一一一一一一1一一一一一一一1一一一一一一一一一一一一一一一一一一一一一一一一1一一一一一一1一1一一一一一一一一一一一一」
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1
∞∞53-OBSV ∞∞∞∞∞∞∞∞∞∞
EFF : ALL Page 101
Feb 01/98
CES
TASK 53-35-00-810-801
1. Possible Causes
R Vibration and/or Noise felt in Mid Cabin _______________
- Aerodynamic Panel-Edge Seals
2. Job Set-up Information
______________________
A. Consumable Materials
-------------------------------------------------------------------------------
REFERENCE DESIGNATION
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Material No. 08-052 USA MIL-T-23397 AND/OR L-T-80B
SELF ADHESIVEALUMINIUM TAPE (Ref. 20-31-00)
B. Referenced Information
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REFERENCE DESIGNATION
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05-50-00-810-801 Identification of the Cause of In-Flight Airframe
Vibrations and/or Noises
R AMM 53-25-11-000-001 Removal of the Wing-to-Fuselage Fairing
R AMM 53-25-11-400-001 Installation of the Wing-to-Fuselage Fairing
AMM 53-35-11-000-001 Removal of the Wing-to-Fuselage Fairings
AMM 53-35-11-400-001 Installation of the Wing-to-Fuselage Fairings
SIL 51-008
3. Fault Confirmation
__________________
A. Procedure
(1) Make sure that the identification of the cause of the vibration is correct.(Ref. TASK 05-50-00-810-801).
(2) If the flight crew have reported vibrations in the center cabin area, do the fault isolation.
4. Fault Isolation_______________
A. Do a visual inspection and check the Aerodynamic Panel-Edge Seals damage, or if they are missing.
(1) If the seals are damaged, or are missing, you must replace the seals (Ref. AMM TASK 53-25-11-000-001) (Ref. AMM TASK 53-25-11-400-001) (Ref. AMM TASK 53-35-11-000-001) (Ref. AMM TASK 53-35-11-400-001) and (Ref. SIL 51-008).
(2) If damage to the seals is not visible but vibration continues, temporarily install high speed tape BONDING AND ADHESIVE COMPOUNDS (Material No. 08-052) over the panel edges.
R R R R NOTE : On panel 191LB the installation of high speed tape is____ permitted to a maximum length of 1250 mm (49.2126 in.). On panel 192LB the installation of high speed tape is permitted to a maximum length of 300 mm (11.8110 in.).
(3) If, after further flight, the vibration no longer exists, remove the high speed tape from one panel.
(4) Repeat Step (3) above after each successive flight until the affected panel is identified.
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