| General | ER/A related | Airworthiness Directive | Service Bulletin | SG Drawings |
|---|---|---|---|---|
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What is a T-tail configuration?
This type of empennage configuration requires stronger design due to increased normal force on the tail and weight of horizontal stabilizer
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What is a straight shank bushing?
This type of repair was used to reinforce oversized hole (s) near the ZFS = 52.276 station
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What is the AD that 2018-10-08 superseded?
AD 2016-09-06
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What is If the Leading Edge skin is not distressed and a crack is found, what type of repair is performed?
The Boeing Company should be contacted for repair instructions.
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What is the maximum number of repair bushings on one side of the splice before a doubler is required in SG95550001?
24 of these are allowed
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What is where would you find the information on Delta requirements for obtaining and using an AMOC?
TOPP 30-20-12
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What is signs (List all signs) of distress in the vertical stabilizer and what can they indicate?
Missing, bushed, or elongated fasteners are signs of distress and can be indicators for undetected cracks in the front spar.
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What is Why the compliance time revised for initial inspection?
This action was taken (in AD 2018-10-08) to address the unsafe condition found with increased cracking instances on V.Stab LE
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What is an FAA Alternative Method of Compliance (AMoC) ?
This document is required to ensure compliance (with AD 2018-10-08) if SB instructions cannot be achieved without deviations
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What is the skin dwg number for bushing cracked holes?
SG95550001 dwg
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What are limit loads?
This is the largest type of load that can be expected during aircraft service, which affects the subject V. Stab LE structure.
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What is the AA number?
5530-01048
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What are the inspections required by the SB when cracking in the vstab is observed?
HFEC and Radio Frequency inspections
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What is Boeing Alert Service Bulletin 717-55A0012?
This document allows for compliance (with AD 2018-10-08), if accomplished without deviations.
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What is the SG drawing that is not included in SB 717-55A0012 and what does it do?
SG95550005 - repairs to the spar cap of the V-stab, Needs Engineering paperwork
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What are two types of skin phenomena observed elsewhere on the A/C occurs along the length of the Front Spar Cap?
The Front Spar Cap is the lap splice for the front of the vertical stabilizer and is a Class 1 Aero-smoothness surface requiring the highest degree of smoothness and uniformity.
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What is In SG Dwg 95550005 providing the bushing/strap repair for the front spar chord near Zfs=52 on the B717 fleet, the existing individually mounted nutplates are removed, and existing nutstrips are trimmed back to allow the repair strap to be fit in. How are the nutplates re-installed?
Contrary to traditional design principles, the nutplates are not re-mounted to a nutstrip or gang channel as was done in the original design, but are installed riveted to the repair strap. To replace a nutplate that may be damaged in the future, the entire repair strap will have to be removed to replace the nutplate.
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What is the reason for AD 2018-10-08 being issued to supersede AD 2016-09-05?
four elongated skin fastener holes and nine cases of spar cap found cracked during initial scheduled inspection
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What is not required per AD 2018-10-08 and can be omitted and/or allow substitutions.
Steps not marked RC in SB 717-55A0012
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What is maximum number of repair bushings allowed per SG95550005 - repair to spar cap?
4 of these are allowed
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What is the reason why do we not have the TOPP reference to set up the AMoC number revised to be correct and not be incorrect, why do we have to use the cheat sheet when it should be per TOPP?
No-one has contacted the owner of the TOPP section to have it corrected.
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What is When repairing structure that has mounted nutplates in the area where your repair parts go, how do you re-mount the nutplates?
To prevent a detrimental fatigue detail in the structure and repair parts caused by the nutplate attach rivets; the nutplates should not be re-mounted with the attach rivets being punched through the full stack-up of original structure and repair parts – or to the repair part only. Nutplates should be mounted to a non-structural strip (commonly referred to as a ‘nutplate strip’ or ‘nut strip’); and then the nut strip mounted to the repaired structure with the structural fasteners attaching the repair parts that are adjacent to the hole location where the nutplate was previously. To replace a nutplate common to the repair that might be damaged in the future, you won’t have to disassemble the repair to get to the nutplate rivets; but merely remove the couple of fasteners attaching the nut strip.
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What does AD 2018-10-08 accomplish?
Revises compliance time to check for cracking on those aircraft that have not had an initial inspection per 2016-09-05
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What is the compliance time for completion of the Part 1 initial inspection of the 717 VStab L/E skin?
15,000 FC or 6,200 FC after AD 2016-09-05, whichever is later. (Src: 717-55A0012)
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What is not required for bolt hole repairs based on SG95550005?
Insurance cut
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