On this page
ADs that cite it · 1
Newest first, with the revision each names, as OpenAirDocs read it from the AD’s text: check it against the AD.
Also cited in 1 proposed AD.
Text · 11
From the PDF’s text layer: layout, tables and figures are lost. The PDF is the document. © Bombardier Inc. Filed by the FAA in regulations.gov docket FAA-2019-0876; AD 2020-05-27 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
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 = '714bf38a1f28a73abbea40bc95a4dba350cbdada3ab9d4006db253bf1950c356' 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 = '714bf38a1f28a73abbea40bc95a4dba350cbdada3ab9d4006db253bf1950c356' 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.
SPECIAL CHECK - AFT FUSELAGE -
INSPECTION OF THE RUDDER QUADRANT BOX ASSEMBLY The information below is provided for your reference. For full details, including labor and part coverage, please see corresponding paragraph contained within this bulletin.
RECOMMENDED
SPECIFIED TIME COMPLIANCE
COMPLIANCE TIME Refer to Paragraph 1.D.
EFFECTIVITY: A/C Serial No. 9002 to 9312, 9314 to 9380 and 9384 to 9429 Pre SB700−53−052 MANPOWER: 1 man−hour
CONTINUED AIRWORTHINESS (CAW)
FLEET CAMPAIGN NOYES TLMC, CH 5 AFFECTED NOYES KITS and/or PARTS NOYES
TOOLING/GSE YES NO PLANNING INFORMATION: See important information at the start of Paragraph 1. YES NO
DEDICATED SCHEDULE NOYES PREREQUISITE SERVICE BULLETINS: N/A NOTE: This Service Bulletin may be subject to an Airworthiness Directive which will make it necessary to implement this Service Bulletin.
To place an order for parts or kits, please call Bombardier Aerospace Parts Services at:
514−855−2999 or 1−866−538−1247
SERVICE BULLETIN SUMMARY my.businessaircraft.bombardier.com MODEL BD−700−1A10 (BD−700) ATA 53−40
FUSELAGE Basic Issue: Oct 01/2018 700−53−054 Page 1 of 1 This Service Bulletin is available at:
SPECIAL CHECK - AFT FUSELAGE -
INSPECTION OF THE RUDDER QUADRANT BOX ASSEMBLY
1. PLANNING INFORMATION NOTES:1 . Before you do this Service Bulletin, examine all STC, STA or equivalent action changes to make sure that this Service Bulletin can be completed.
2. For aircraft that have complied with SB 700−53−052, this Service Bulletin is not applicable.
A. Effectivity BD−700−1A10 aircraft, Serial No. 9002 to 9312, 9314 to 9380 and 9384 to 9429 Pre SB 700−53−052.
B. Reason
1. Condition:
Cracking was discovered on the AFT lower half−rib, Part No. GD417−1539−1, and the FWD upper half rib, Part No. GD417−1588−3. These half−ribs are part of the Rudder Quadrant Box Assembly.
2. Evidence:
Cracks initiating from rivet holes on the FWD upper half rib’s and the AFT lower half rib’s attachment flange to the LH channel were discovered. In addition, cracks were also discovered at the radius of the FWD upper half rib’s and the AFT lower half rib’s attachment flange to the LH channel.
SERVICE BULLETIN my.businessaircraft.bombardier.com MODEL BD−700−1A10 (BD−700) ATA 53−40
FUSELAGE Refer to applicable governmental agency regulations and requirements and make sure that the work described in this Service Bulletin is performed in compliance with manufacturer’s recommendations and/or acceptable industry standards.
This document is proprietary to Bombardier Inc. and/or its affiliates and may not be reproduced or copied in any form or by any means without the prior written consent of Bombardier Inc. and/or its affiliates.
2018 Bombardier Inc. All rights reserved Learjet, Challenger, Global, are registered trademarks of Bombardier Inc. or its subsidiaries.
Basic Issue: Oct 01/2018 700−53−054 Page 1 of 8 This Service Bulletin is available at:
3. Objective/Benefit:
Because no−part specific inspection exists for this area, cracking could go undetected. This Service Bulletin gives instructions to inspect the structure of the Rudder Quadrant Box Assembly in a specific area for cracks, and also provides adequate instructions if cracks are found.
C. Description This Service Bulletin gives instructions to:
− Open the Aft Equipment−Compartment door 311BB, − Do the inspection as instructed, and − Take the appropriate action.
D. Compliance Specified Time Compliance is as follows:
Initial inspection − Aircraft with 2000 flight cycles or more from C of A, at the time of release of this Service Bulletin (Basic Issue), must complete the inspection within 100 flight cycles.
− Aircraft with less than 2000 flight cycles from C of A, at the time of release of this Service Bulletin (Basic Issue), must complete the inspection within 1000 flight cycles.
Repeat inspection − Aircraft with less than 2000 flight cycles from C of A, at the time of release of this Service Bulletin (Basic Issue) and that have completed the initial inspection, must repeat the inspection every 1000 flight cycles, up to 3000 accumulated flight cycles from C of A.
NOTES: 1. When the aircraft reaches 3000 accumulated flight cycles from C of A or reaches 60 months from the release date of SB 700−53−052 (Basic Issue), whichever comes first, SB 700−53−052 must be incorporated.
2. If it is not possible to complete all the instructions in this Service Bulletin because of the aircraft configuration, submit an SRPSA for analysis and to get an approved disposition to complete this Service Bulletin.
E. Approval This Service Bulletin does not contain modification information that revises the approved configuration and therefore does not require governmental or other regulatory approval.
MODEL BD−700−1A10 (BD−700) Basic Issue: Oct 01/2018 700−53−054 Page 2 of 8
F. Manpower NOTES: 1. The man−hours given are to help you schedule the tasks given in this Service Bulletin. The man−hours are for direct labor performed by an experienced crew and do not include the time for familiarization, planning, aircraft preparation in hangar such as towing and positioning of scaffolds, removal of interior furnishings, repainting, supervision and inspection.
For more information related to the manpower, refer to SB 700−00−002.
1 man−hour is necessary to do this Special Check.
Bombardier Aerospace does not pay for the labor to do this Special Check.
G. Material − Cost and Availability No kit or parts are necessary to do this Special Check. For material data, refer to Paragraph 3.
H. Tooling The equipment and tools listed below are necessary to do this:
GSE REFERENCE NO. PART NO. DESCRIPTION 24−00−24 S4933959−501 Tag, Circuit Breaker Commercially Available − 10X, Magnifying Glass I. Weight and Balance No change.
J. Electrical Load Data No change.
K. References − Bombardier Aerospace, Restriction and/or Special Instruction (RSI), C−01705, Rev. A.
− Advisory Wire AW700−53−0585.
− Global Express BD−700 Aircraft Maintenance Manual (AMM), Chapters 6, 24 and 27.
L. Other Publications Affected None.
MODEL BD−700−1A10 (BD−700) Basic Issue: Oct 01/2018 700−53−054 Page 3 of 8
M. Equivalent Service Bulletins For the Global 5000 BD−700−1A11 aircraft, use SB 700−1A11−53−029.
For the Global 5000 BD−700−1A11 Featuring Global Vision Flight Deck aircraft, use SB 700−53−5013.
For the Global 6000 BD−700−1A10 aircraft, use SB 700−53−6012.
2. ACCOMPLISHMENT INSTRUCTIONS NOTES: 1. All TASKs given in the procedures that follow are from the Global Express or Global Express XRS BD−700−1A10, Aircraft Maintenance Manual (AMM) unless otherwise specified.
2. All references made to zones, access panels and/or doors, are from the Global Express or Global Express XRS BD−700−1A10 Aircraft Maintenance Manual (AMM), Chapter 6.
A. Aircraft Setup NOTE: The steps in the Aircraft Setup section of this Service Bulletin are recommended steps. The steps give a recommendation to get access to the work area. This recommendation is to give a safe work area and to minimize possible damage to surrounding aircraft parts. Alternative steps can be used at the operator’s discretion.
(1) Obey all electrical/electronic safety precautions. Refer to AMM 24−00−00−910−801.
(2) Obey all flight control safety precautions. Refer to AMM 27−00−00−910−801.
(3) Open the Aft Equipment−Compartment Door 311BB.
B. Inspection NOTE: If it is not possible to complete all the instructions in this Service Bulletin because of the configuration of the aircraft, submit an SRPSA for analysis and to get an approved disposition to complete this Service Bulletin.
(1) Perform a Detailed Visual Inspection for cracks at 10X magnification at the locations that follows:
(a) At location 1, where the FWD upper half rib, Part No. GD417−1588−3 attaches to the LH channel, Part No. GD417−1520, refer to Figure 1, do as follows:
(i) Inspect all parts at this location for visible cracks near the attachment fasteners. Pay special attention for cracks in the radius of the attachment flange on the FWD upper half rib.
(ii) Cracks that are less than 1.20 in (30.48 mm) in length on the FWD upper half rib are considered to be within acceptable limits.
MODEL BD−700−1A10 (BD−700) Basic Issue: Oct 01/2018 700−53−054 Page 4 of 8
(iii) If a crack of 1.20 in (30.48 mm) or more in length is found on the FWD upper half rib, SB 700−53−052 must be completed within 100 Flight Cycles from the discovery of the damage.
(b) At location 2, where the AFT lower half rib, Part No. GD417−1539−1, attaches to the LH channel, Part No. GD417−1520, refer to Figure 1, do as follows:
(i) Inspect all parts at this location for visible cracks near the attachment fasteners. Pay special attention for cracks in the radius of the attachment flange of the AFT lower half rib.
(ii) Cracks that are less than 0.40 in (10.16 mm) in length on the AFT lower half rib are considered to be within acceptable limits.
(iii) If a crack of 0.40 in (10.16 mm) or more in length is found on the AFT lower half rib, SB 700−53−052 must be completed within 100 Flight Cycles from the discovery of the crack.
(c) At location 3, refer to Figure 1 and Figure 2, do as follows:
(i) Check for any visible cracks that may exist in the LH channel, Part No. GD417−1520, in the area of the rib attachments on both side of the LH channel.
(ii) No cracks are allowed in the LH channel.
(iii) If a crack is found in the LH channel, Part No. GD417−1520, SB 700−53−052 must be completed within 100 Flight Cycles from the discovery of the crack.
C. Close−out NOTE: The steps in the Close−out section of this Service Bulletin, except for the return−to−service tests, are recommended steps. The steps give a recommendation to install components removed during the Aircraft Setup.
This recommendation is to make sure that the aircraft is safe and ready to return to service. Alternative steps can be used at the operator’s discretion.
(1) Remove all tools, equipment and unwanted materials from the aircraft.
(2) Close the aft equipment compartment door 311BB.
D. Recording When this Service Bulletin is completed, make an entry in the aircraft log and send the attached Incorporation Notice to Bombardier Business Aircraft Customer Services (BBACS).
In an effort to improve the quality of our technical communications, we are requesting your feedback. Please take a moment to fill out our easy on−line Service Bulletin survey:
http://csefeedback.aero.bombardier.com MODEL BD−700−1A10 (BD−700) Basic Issue: Oct 01/2018 700−53−054 Page 5 of 8
3. MATERIAL INFORMATION A. Kit No kits required.
B. Parts No parts required.
C. Material No consumables are required.
D. Publications No publications required.
MODEL BD−700−1A10 (BD−700) Basic Issue: Oct 01/2018 700−53−054 Page 6 of 8
GSB5340_071
2.00 in.
(50.80 mm)
2.00 in.
(50.80 mm) LOCATION 1 LOCATION 2 LOCATION 3
LH CHANNEL GD417−1520 RUDDER QUADRANT BOX ASSEMBLY (GD419−1515) (Top skin not shown for clarity)
LH CHANNEL GD417−1520 INSPECTION LOCATIONS 1, 2 and 3
VIEW LOOKING OUTBOARD ON THE LH CHANNEL OF THE RUDDER QUADRANT
BOX ASSEMBLY AT THE AIR SYSTEMS SUPPORT FITTING LOCATION
FWD UPPER
HALF RIB GD417−1588AFT LOWERHALF RIB GD417−1539
AFT LOWER
HALF RIB GD417−1539
FWD UPPER
HALF RIB GD417−1588 MODEL BD−700−1A10 (BD−700) Figure 1 − Inspection Locations Basic Issue: Oct 01/2018 700−53−054 Page 7 of 8
GSB5340_081
RUDDER QUADRANT BOX ASSEMBLY
EXISTING AIR SYSTEMS SUPPORT FITTING GD437−1585 (REF)
LH CHANNEL GD417−1520 LOCATION 3
AIR SYSTEMS SUPPORT FITTING GD437−1585
2.00 in.
(50.80 mm)
2.00 in.
(50.80 mm) INSPECTION LOCATION 3
VIEW LOOKING INBOARD ON THE LH CHANNEL OF THE RUDDER QUADRANT
BOX ASSEMBLY AT THE AIR SYSTEMS SUPPORT FITTING LOCATION
RUDDER QUADRANT
BOX ASSEMBLY GD419−1515 MODEL BD−700−1A10 (BD−700) Figure 2 − Inspection Location Basic Issue: Oct 01/2018 700−53−054 Page 8 of 8
700−53−054 Basic Oct 01/2018 SPECIAL CHECK − AFT FUSELAGE −
INSPECTION OF THE RUDDER QUADRANT BOX ASSEMBLY In an effort to improve the quality of our technical communications, we are replacing the standard Service Bulletin Evaluation Form with an on−line Service Bulletin Survey and we are requesting your feedback. Please take a moment to fill out our easy on−line Service Bulletin survey at:
http://csefeedback.aero.bombardier.com
SERVICE BULLETIN EVALUATION FORM (Your ideas will help us provide better bulletins) SERVICE BULLETIN: ISSUE: DATED:
TITLE:
SERVICE BULLETIN INCORPORATION SHEET − "700−53−054" Upon completion of the Service Bulletin, please fill−in, fax to
(514) 855−8798 or e−mail to Fracas at fracas.montreal@aero.bombardier.com If you’re reporting Service Bulletin (SB) Incorporations to CAMP, sending this Incorporation Sheet to Bombardier is not mandatory. If your aircraft is on another tracking system, please contact Bombardier to make arrangements for automated data submission.
700−53−054 Basic
COMPLIED WITH
YES NO N/A Actual hours to accomplish Service Bulletin:
* NOTES:
Aircraft Serial No. Aircraft Reg. No.
Airframe Hours: Airframe Landings S.B. Incorporation Date Service Order No.
Facility incorporating S.B.
Name Signature Date
BOMBARDIER
SUBMISSION Service Bulletin Number Rev. * Parts Completed Remarks/Reason (Mandatory if N/A)
1. Where the Service Bulletin is divided into a number of parts (e.g., PARTS A, B, C, D, etc.) which can be carried out separately, indicate only those parts completed at this time.
2. For repetitive checks (usually PART A) only the initial check should be reported unless otherwise stated in the Service Bulletin.
3. When more than one part is carried out at the same time, each part should be reported.
4. Fill in ’Remark/Reason’ to explain compliance method when N/A is selected.(E.g. Part not installed, N/A by effectivity, N/A by Part Serial Number, etc.
5. PCW means ’Previously Complied With’.
(dd/mm/yy) Signature not required if sent by E−Mail (dd/mm/yy)