TextPartly OCR
Some pages are OCR from a scan. OCR can misread letters and numbers.
Query with SQL
duckdb -csv -c "SELECT p.page, p.text_source, p.text, f.rights_holder, f.license FROM 'https://openairdocs.org/data/latest/service_document_file_page.parquet' p JOIN 'https://openairdocs.org/data/latest/service_document_file.parquet' f USING (file_sha256) WHERE p.file_sha256 = '6faa59b4754665d6ef1d61c037fc201ff90aea471c662058f76a7796bab5561f' ORDER BY p.page"
Prints the whole list as CSV. It reads the release’s Parquet files over HTTPS, so there’s nothing to download first. Install DuckDB to run it.
SELECT p.page, p.text_source, p.text, f.rights_holder, f.license FROM 'https://openairdocs.org/data/latest/service_document_file_page.parquet' p JOIN 'https://openairdocs.org/data/latest/service_document_file.parquet' f USING (file_sha256) WHERE p.file_sha256 = '6faa59b4754665d6ef1d61c037fc201ff90aea471c662058f76a7796bab5561f' ORDER BY p.page
Run it at the DuckDB prompt, or in any tool that reads Parquet over HTTPS. More ways to query the release are on Use the data.
CUSTOMER BULLETIN
SUBJECT
NUMBER 223
FLIGHT CONTROLS (ATA 27)
INSPECTION - FLIGHT CONTROL SURFACES
PAINT THICKNESS
MARCH 23, 2012
Gulfstream IV Customer Bulletin No. 223 “March 23, 2012”
Page 1 of 8 Flight Controls (ATA 27), Inspection – Flight Control Surfaces Paint Thickness
I. Planning Information:
A. Effectivity:
Aircraft serial numbers 1265, 1286, 1298, 1301, 1347, 1372, 1378, 1380, 1423, 1458 and 1497 B. Reason:
Gulfstream has determined through routine records review that, during application, the flight control surfaces paint thickness may not have been properly documented on a number of aircraft. Excessive paint thickness will affect the balance moment of the flight control surface and may result in reduced control surface flutter margin.
C. Description:
This customer bulletin is divided into two parts:
Part I of this customer bulletin is a one-time action to inspect the flight control surface paint thickness on identified aircraft and to incorporate Airplane Flight Manual Supplement (AFMS) GIV-2012-01 imposing altitude restrictions for any aircraft found to have excessive paint.
Part II of this customer bulletin is a one-time action to correct any excessive paint thickness conditions identified by the Part I inspection. This part will also remove the AFMS altitude restrictions upon completion of corrective action.
Note: All references in this document are intended to be inclusive of any amendments or revisions unless otherwise stated.
D. Compliance:
Compliance with Part I of this customer bulletin is required within 180 days of the release date.
Compliance with Part II of this customer bulletin, if necessary, is required within 12 months from compliance with Part I of this customer bulletin.
This customer bulletin is a managed program and should be accomplished at a Gulfstream Aerospace Authorized Warranty Repair Facility. Compliance with this customer bulletin must be coordinated through Gulfstream Scheduling at 800-810-GULF (4853), or 912-965-4178. If not scheduled, down times could increase significantly.
E. Approval:
This customer bulletin has been FAA approved as this issue is the subject of FAA Airworthiness action. It does not contain any modification information nor revise the approved configuration and as such does not require any other regulatory approval.
Gulfstream IV Customer Bulletin No. 223 “March 23, 2012”
Page 2 of 8 F. Manpower:
Inspection (Part I) - 4.5 man-hours Note: Listed man-hours are for Part I inspection only. Due to the potential variation of work requirements to correct any deficiencies, labor coverage for Part II corrective action must be charged on a separate work order and submitted for warranty consideration.
G. Material:
None H. References:
GIV Aircraft Maintenance Manual (AMM), Chapters 20 and 27 GIV Airplane Flight Manual (AFM) GIV Airplane Flight Manual Supplement (AFMS) GIV-2012-01 (attached) Gulfstream Aerospace Material Process Specification (GAMPS) 4000, revision F I. Tooling/Equipment:
Ultrasonic Coating Thickness Gage, Positector 200 series or equivalent J. Opportunity for No-Charge Compliance:
Labor and material will be provided at no charge if this customer bulletin is accomplished within the recommended compliance time, as stated in this document, at a Gulfstream IV Authorized Warranty Repair Facility.
Note: Additional labor hours incurred due to aircraft configuration or mechanical difficulties must be charged on a separate work order and submitted for warranty consideration.
Note: Labor and materials for corrective action (Part II), if necessary, must be charged on a separate work order and submitted for warranty consideration.
K. Weight and Balance:
N/A Part I II. Accomplishment Instructions:
CAUTION: PROTECT WIRE BUNDLES, CONNECTORS AND SURROUNDING
STRUCTURE DURING ANY MAINTENANCE PROCEDURE FROM SHAVINGS, DEBRIS AND CONTAMINATION. MAINTAIN A PROPERLY CLEANED WORK
AREA THROUGHOUT THE PROCEDURE TO ENSURE THE INTEGRITY OF THE AFFECTED COMPONENT / SYSTEM. VISUALLY INSPECT WORK AREA
USING ADDITIONAL LIGHT AS NECESSA RY TO VERIFY ABSENCE OF ANY DEBRIS PRIOR TO COMPLETION OF PROCEDURE. FAILURE TO COMPLY MAY RESULT IN DAMAGE TO COMPONENTS AND / OR SYSTEMS.
Gulfstream IV Customer Bulletin No. 223 “March 23, 2012”
Page 3 of 8 A. Prepare the aircraft for safe maintenance as follows:
1. Remove electrical power, turn all cockpit switches off and disconnect battery quick disconnects.
B. Gain access to all flight control surfaces (aileron, rudder and elevator).
C. Using the paint thickness measurement maps (Tables 1, 2 and 3) mark the reading points on both sides of each flight control surface.
D. Using an ultrasonic coating thickness gage, Positector 200 series or equivalent, measure the paint thickness on the flight control surfaces at each reading point as shown on the paint thickness measurement map for each respective flight control surface. Record readings on the appropriate tables. See Tables 1, 2 and 3.
E. Calculate the average paint thickness for each surface by adding all of the readings for that surface and dividing by the number of readings. For example, in Table 1 the left aileron point readings for mid-chord and rear, upper and lower surfaces would be totaled and then divided by 24, which is the number of reading points.
F. Table 4 contains maximum allowable paint thickness averages for individual aircraft serial numbers. These thickness allowances have been determined using historical balance information for each individual flight control surface to determine maximum paint thickness that could be applied without negatively affecting the balance moment, and are not required paint thicknesses. Confirm part number and serial number of the respective flight control surface prior to using the values on this chart. If the part number and/or serial number do not match the chart information, default values of 5.0 mils must be used.
G. Compare average paint thickness recorded on Tables 1, 2 and 3 with the maximum allowable paint thickness average for each flight control surface shown in Table 4. For each flight control surface perform the following:
1. If average paint thickness is equal to or less than 5.0 mils – no further action is required, proceed to Step II.H. Report Part II of this customer bulletin as “Not Applicable – No action required from Part I.”
2. If average paint thickness is greater than 5.0 mils, but equal to or less than the serial number specific allowances provided in Table 4 - no further action is required, proceed to Step II.H. Report Part II of this customer bulletin as “Not Applicable – No action required from Part I.”
3. If average paint thickness is greater than the serial number specific allowances provided in Table 4, but less than 13 mils – Incorporate AFMS GIV-2012-01 into the Airplane Flight Manual for continued operation at or below 41,000 feet until condition is corrected. Compliance with Part II of this customer bulletin is required within 12 months from compliance with Part I.
4. If average paint thickness is greater than the serial number specific allowances provided in Table 4, and exceeds 13.0 mils – Continued operation is not allowed, contact Gulfstream Customer Support for instructions on compliance with Part II of this customer bulletin.
Gulfstream IV Customer Bulletin No. 223 “March 23, 2012”
Page 4 of 8 H. Ensure work area is clean and clear of foreign objects (FOD).
I. Record compliance with Part I of this customer bulletin in the aircraft’s permanent maintenance records and return aircraft to flight status.
J. Report compliance with Part I of this customer bulletin to Gulfstream Computerized Maintenance Program (CMP) via electronic transmittal or fill out and fax the attached service reply card.
Part II III. Accomplishment Instructions CAUTION: PROTECT WIRE BUNDLES, CONNECTORS AND SURROUNDING
STRUCTURE DURING ANY MAINTENANCE PROCEDURE FROM SHAVINGS, DEBRIS AND CONTAMINATION. MAINTAIN A PROPERLY CLEANED WORK
AREA THROUGHOUT THE PROCEDURE TO ENSURE THE INTEGRITY OF THE AFFECTED COMPONENT / SYSTEM. VISUALLY INSPECT WORK AREA
USING ADDITIONAL LIGHT AS NECESSA RY TO VERIFY ABSENCE OF ANY DEBRIS PRIOR TO COMPLETION OF PROCEDURE. FAILURE TO COMPLY MAY RESULT IN DAMAGE TO COMPONENTS AND / OR SYSTEMS.
A. Prepare the aircraft for safe maintenance as follows:
1. Remove electrical power, turn all cockpit switches off and disconnect battery quick disconnects.
B. For affected surfaces having an overall average thickness greater than the values shown on Table 4 as described in Part I, Steps II.G.3. and II.G.4., one of the following corrective actions shall be required within the specified compliance time. Contact Gulfstream Customer Support for assistance in determining the appropriate corrective action.
1. Remove flight control surface and rebalance per AMM, Chapter 27.
2. Strip and repaint with average thickness less than 5.0 mils. Re-measure thickness.
Refer to GAMPS 4000, revision F.
3. Sand/buff down to 5.0 mils or less and re-measure thicknesses (not recommended on surfaces with averages exceeding 7.0 mils). Refer to GAMPS 4000, revision F.
C. Remove Airplane Flight Manual Supplement GIV-2012-01 from the Airplane Flight Manual.
D. Ensure work area is clean and clear of foreign objects (FOD).
E. Record compliance with Part II of this customer bulletin in the aircraft’s permanent maintenance records and return aircraft to flight status.
F. Report compliance with Part II of this customer bulletin to Gulfstream Computerized Maintenance Program (CMP) via electronic transmittal or fill out and fax the attached service reply card.
If technical assistance is required, contact your area Gulfstream Field Service Representative or call Gulfstream Customer Support at 800-810-GULF (4853) or 912-965-4178 (fax 912-965-4184).
Gulfstream IV Customer Bulletin No. 223 "March 23, 2012" REAR PAINT THICKNESS READINGS (MIL,0.001") RIGHT HAND -aIW -aIW REAR REAR LOWER
PAINT THICKNESS MEASUREMENT MAP MEASUREMENTS COLLECTED BY INSTRUMENT AND CAL EXPIRY LEFT HAND MID- REAR CHORD N/A N/A N/A N/A AIRCRAFT S/N SITE/REPAIR STATION DATE PAINT TYPE UPPER PT MID- CHORD N/A N/A N/A N/A AVG Aileron Measurement Map Table 1
INBOARD OUTBOARD MID-CHORD 4 PT @ 8" SPACING REAR 8 PT @ 4" SPACING DEVIATIONS UP TO 1 INCH RADIUS FROM THE POINTS SHOWN ARE ACCEPTABLE
AILERON
LH SHOWN RH SIMILAR Page 5 of 8
Gulfstream IV Customer Bulletin No. 223 "March 23, 2012"
RIGHT HAND MID- PAINT THICKNESS READINGS (MIL,0.001") -aIW REAR LOWER
PAINT THICKNESS MEASUREMENT MAP MEASUREMENTS COLLECTED BY INSTRUMENT AND CAL EXPIRY LEFT HAND MID- REAR CHORD N/A N/A N/A N/A N/A N/A N/A N/A AIRCRAFT S/N SITE/REPAIR STATION DATE PAINT TYPE UPPER PT MID- CHORD OL IN/A 11 N/A 12 VIN 13 N/A 14 N/A 15 VIN
INBOARD OUTBOARD MID-CHORD 8 PT @ 24" SPACING REAR 16 PT @ 12" SPACING LH SHOWN RH SIMILAR DEVIATIONS UP TO 1 INCH RADIUS FROM THE POINTS SHOWN ARE ACCEPTABLE Page 6 of 8
Gulfstream IV Customer Bulletin No. 223 "March 23, 2012" PAINT THICKNESS READINGS (MIL, 0.001") RIGHT HAND MID- REAR CHORD
SITE/REPAIR STATION MEASUREMENTS COLLECTED BY INSTRUMENT AND CAL EXPIRY LEFT HAND MID- REAR CHORD AIRCRAFT S/N DATE PAINT TYPE PT 100 10 11 AVERAGE PAINT THICKNESS MEASUREMENT MAP Upper Lower Rudder Measurement Map MID-CHORD 6 PT @ 24" SPACING REAR 12 PT @ 12" SPACING Table 3 RUDDER DEVIATIONS UP TO 1 INCH RADIUS FROM THE POINTS SHOWN ARE ACCEPTABLE Page 7 of 8
Gulfstream IV Customer Bulletin No. 223 "March 23, 2012" SIN
RUDDER P/N S/N
ELEVATOR RH P/N Allowable Coating (mil) 5.0 Default 5.0 Default 6.5 5.0 Default 5.0 Default 5.0 Default 5.0 Default 5.0 Default 5.0 Default 5.0 Default 5.0 Default TOTAL COATING ALLOWANCE (MIL) ELEVATOR LH SIN P/N 1159CS20002-29 Note: Confirmation of part number and serial number must be made. If not corresponding with Table, default to 5.0 mil allowance Allowable Paint Thickness Allowable Coating (mil) 5.0 Default 5.0 Default 5.3 5.0 Default 5.0 Default 5.0 Default 5.0 Default 5.0 Default 5.0 Default 5.0 Default 5.0 Default Table 4 S/N
AILERON RH P/N Allowable Coating (mil) 5.0 Default 5.0 Default 5.0 Default 5.0 Default 5.0 Default 5.0 Default 5.0 Default 5.0 Default 5.0 Default 5.0 Default 5.0 Default
CONTROL SURFACE COATING ALLOWANCE -S/N SPECIFIC S/N
AILERON LH P/N Allowable Coating (mil) 5.0 Default 5.0 Default 5.0 Default 5.0 Default 5.0 Default 5.0 Default 5.0 Default 5.0 Default 5.0 Default 5.0 Default 5.0 Default Model GIV GIV GIV GIV GIV GIV GIV GIV GIV GIV GIV A/C S/N 1265 1347 1372 1378 1380 1497 Page 8 of 8
Gulfstream IV Customer Bulletin No. 223 “March 23, 2012”
Customer Bulletin prepared by Gulfstream Aerospace, 500 Gulfstream Road, P.O. Box 2206, Savannah, Georgia 31402-2206, USA.
© 2012 Gulfstream Aerospace All rights reserved, including the right to reproduce this publication. No part may be reproduced, stored in any retrieval system, or transmitted in any part or form or by any means, electronic, photocopying, microfilm, microfiche, mechanical, or otherwise, without prior written permission of Gulfstream Aerospace.
This technical data is controlled under the Export Administration Regulations by General License TSU. It may not be transferred to a third party without the prior written approval of the U.S. Department of Commerce.
GA 611A 2/97 Part I Service Reply Card
Please fax this page to Gulfstream CMP at 800-944-1775 or 912-963-0265.
The following Customer Bulletin (CB) has been addressed:
CB Number A/C A/C Type Compliance Date 982230 GIV
Aircraft Hours Aircraft Landings
This Customer Bulletin is not applicable because:
Serial Number not affected Appliance not installed ______Previously complied with (annotate method of compliance below)
Signature Title/Certificate Number Company
Comments / Suggestions:
Gulfstream IV Customer Bulletin No. 223 “March 23, 2012”
Customer Bulletin prepared by Gulfstream Aerospace, 500 Gulfstream Road, P.O. Box 2206, Savannah, Georgia 31402-2206, USA.
© 2012 Gulfstream Aerospace All rights reserved, including the right to reproduce this publication. No part may be reproduced, stored in any retrieval system, or transmitted in any part or form or by any means, electronic, photocopying, microfilm, microfiche, mechanical, or otherwise, without prior written permission of Gulfstream Aerospace.
This technical data is controlled under the Export Administration Regulations by General License TSU. It may not be transferred to a third party without the prior written approval of the U.S. Department of Commerce.
GA 611A 2/97 Part II Service Reply Card
Please fax this page to Gulfstream CMP at 800-944-1775 or 912-963-0265.
The following Customer Bulletin (CB) has been addressed:
CB Number A/C A/C Type Compliance Date 982231 GIV
Aircraft Hours Aircraft Landings
This Customer Bulletin is not applicable because:
Serial Number not affected No action required from Part I ______Previously complied with (annotate method of compliance below)
Signature Title/Certificate Number Company
Comments / Suggestions:
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL SUPPLEMENT NO. GIV-2012-01 Gulfstream Aerospace Corporation Supplement No. GIV-2012-01 P.O. Box 2206 Savannah, Ga. 31402-2206
FAA APPROVED
AIRPLANE FLIGHT MANUAL
SUPPLEMENT FOR
GULFSTREAM MODEL GIV REGISTRATION NUMBER:
SERIAL NUMBER:
This Supplement must be attached to the FAA Approved GIV Airplane Flight Manual, dated 22 April 1987, for GIV airplanes found to have excessive paint thickness on the flight control surfaces (S/N 1265, 1286, 1298, 1301, 1347, 1372, 1378, 1380, 1423, 1458, and 1497).
The information contained herein supplements or supersedes the information of the basic Airplane Flight Manual. For Limitations, Normal Procedures, Abnormal Procedures, Emergency Procedures and Performance information not contained in this supplement, consult the basic Airplane Flight Manual.
FAA APPROVED: Naun M Sapley L William S. Whitton, Jr.
ODA Lead Administrator ODA-511131-CE DATE: March 13,2012