copies of Attachment I and/or II.
2) What are the locations of any unique external features such as external doublers, skin patches or dents on the fuselage or wing surfaces? 3) Did any maintenance action precede the initial report of vibration? What maintenance action was taken during the diagnosis of the vibration?
500
May 01/00 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 5-51-281 Page 203
This guide has been compiled to aid in troubleshooting airframe vibrations on 737-100/-200 airplanes. The guide is divided into two levels of inspections and tests. Level I checks might be used during a sensory check of the airplane after the first flight squawk. Level II check are more in-depth and require more time to perform.
LEVEL II: Inspections and Tests - Initial report may specify vibration type and/or location, or flight condition - Inspections and tests require removal of panels, taking measurements, performing ground tests, etc.
LEVEL I - GENERAL INSPECTIONS LEVEL II - INSPECTIONS AND TESTS
LEVEL I: General Inspections - Performed on Ground - Initial report may not specify vibration type or location.
REPORTED VIBRATION INSPECTION LOCATION
Reported high frequency vibration that is usually manifested as a sound but in some cases might be felt. The vibration can be constant during all phases of flight or may vary with increased airspeed. Check for the following: 1. Missing sealant at the wing-to-body fairing (typical IPC 53-50-0-10, Item 10). 2. Discrepant ground service swing check valve per MM 21-21-11. 3. Ram air inlet deflector door for looseness per
Vibration might be heard/felt in a
specified location or may be MM 21-52-21.
transmitted to a broad area of the airframe. 4. Ram air exhaust modulation louver assembly per MM 21-52-91.
5. Mis-adjusted nose landing gear doors per MM 32-22-11. 6. Mis-adjusted main landing gear strut and wing doors per MM 32-13-11 and 32-13-21. 7. Damaged, mis-faired or malfunctioning lower fuselage doors, access panels and hatches including landing gear and cargo doors, ground service access panels, maintenance compartment access hatches and any missing or delaminated panels. Also check all panels and components in and around the engines. Reference MM 52-31-0 (cargo door), 52-48-11 (A/C access doors), 52-48-21 (APU access door), 52-48-31 (lower nose compartment access door), 52-48-41 (E.E. bay access door), 52-49-0 (misc. doors).
Reported high frequency vibration Check for the following:
that is usually manifested as a sound but in some cases might be felt. The vibration can be constant during take-off or approach when flaps are out. Vibration can be heard/felt in the wing 1. Loose attachment bolts on the hinged flap carriage rollers per MM 27-51-51. 2. Play in the trailing edge inboard flap aft segment caused by wear or deterioration of the aft segment actuation mechanism cam roller bearing and drum assembly
root area. components. These components are located on the inboard end of the midflap segment (typical IPC 57-53-2-14A, Item 85, 86, 225, and 230). 3. Separation or deterioration of the foreflap/spoiler interface blade seal per MM 27-61-11 figure 401.
Vibration Troubleshooting Guide 500
5-51-281 Figure 201 (Sheet 1) May 01/00
Page 204
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
The following matrix can be used after receiving a vibration report that specifies location and type of vibration. The numbers in the matrix relates to "Check Numbers" found in LEVEL II - Inspections and Tests.
VIBRATION TYPES AND LOCATIONS
REPORTED VIBRATION TYPE CREW COMPARTMENT PASSENGER COMPARTMENT - OVERWING PASSENGER COMPARTMENT - GENERAL AFT EMPENNAGE
HIGH FREQUENCY - VIBRATION 103, 106 101, 102 101, 102 106
LOW FREQUENCY VIBRATION ASSOCIATED WITH FEEL 100, 106, 107 100 100, 104 100, 106, 107
HIGH FREQUENCY VIBRATION ASSOCIATED WITH SOUND AND FEEL 103 101, 102, 105 101, 102, 105
LEVEL II - INSPECTIONS AND TESTS VIBRATION TROUBLESHOOTING
Check Number CHECKS AND SYMPTONS INSPECTIONS/TESTS/MAINTENANCE
100 Airplane reported as "buffeting". Do the following: 1. Check body/wing and tail for excessive or large dents/patches and bulges. Pay particular attention to the leading edge devices. The leading edge devices should be undamaged and free of patches and dents. The condition of the leading edges have a significant effect on high speed buffet characteristics. Refer to Structural Repair Manual (SRM) 57-50-1 for maximum allowable damage. 2. Check that the wing vortex generators are undamaged and are properly positioned on the airplane per Dispatch Deviations Procedure Guide, Section 3, Item No. 57-30-6, page 3.57.9. 3. Check leading edge flaps and slats for proper fair and adjustment. Pay particular attention to fair of slat with wing leading edge when leading edge devices are retracted. Mismatch of slat upper trailing edge has significant effect on airplane high speed buffet characteristics. Inspect per MM 27-81-0. 4. Check condition of spoiler panel to flap seals. Inspect per MM 27-61-11. 5. Check both captain's and first officer's airspeed/mach and altimeter readings are accurate per MM 34-12-0. 6. Perform full range leakage ground tests of captain's and first officer's pitot static systems per MM 34-11-00. 7. Verify that the proper pitot static probes are installed in four places (typical IPC 34-10-0-2, Item 15 and 20.
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