Airworthiness directives › 2016-25-25
AD 2016-25-25 Airworthiness Directives; BAE Systems (Operations) Limited Airplanes
Models named: 4101. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to BAE Systems (Operations) Limited Model 4101 airplanes, certificated in any category, all models and all serial numbers.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
Within 30 days after February 7, 2017 (the effective date of this AD), or within 1,600 flight cycles since the most recent detailed inspection was done as specified in BAE Systems Alert Service Bulletin J41-A57-029, whichever occurs later: Do a detailed inspection for cracks, corrosion, and other defects (defects include scratches, dents, holes, damage to fastener holes, or damage to surface protection and finish) of the rear face of the wing rear spars, in accordance with the Accomplishment Instructions of BAE Systems Alert Service Bulletin J41-A57-029, Revision 3, dated April 8, 2014. Repeat the inspection thereafter at intervals not to exceed 1,600 flight cycles. (1) If any cracking, corrosion, or other defect is found within the criteria defined in Chapter 57, Wings, of the Jetstream Series 4100 Structural Repair Manual (SRM), Volume 1, Publication Ref. No. (Transmittal No.) SA 4-4100/SRM/400, Revision 32, dated October 15, 2014 (“Chapter 57 of the SRM”): Before further flight, repair the affected area, in accordance with the repair instructions of Chapter 57 of the SRM. (2) If any cracking, corrosion, or other defect is found exceeding the criteria defined in Chapter 57 of the SRM: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or BAE Systems (Operations) Limited's EASA Design Organization Approval (DOA).
Unsafe condition
This AD was prompted by new reports of cracking found in the wing rear spar and technical analysis results, which confirmed that the crack initiation and propagation are due to fatigue, with no indication of any other crack initiation mechanism ( e.g., stress corrosion). We are issuing this AD to detect and correct cracking in the wing rear spar, which could propagate to a critical length, possibly affecting the structural integrity of the area and resulting in a fuel tank rupture, with consequent damage to the airplane and possible injury to its occupants.
Affected ADs
This AD replaces AD 2012-11-15, Amendment 39-17079 (77 FR 36127, June 18, 2012) (“AD 2012-11-15”).
Read the original on the Federal Register →
You just looked this one up by hand
TrackAD holds all 12,278 of them and matches them against the aircraft you actually look after — airframe, engine, propeller and appliances in one pass — then works out what falls due and when.
- Bring your existing list in from a spreadsheet Paste the rows straight out of Excel. Headers like C/W Date and N/A are read for you.
- A copy that works when this does not One file. No internet, no login, no this software running. For the morning something has to be produced and the computer is not cooperating.
- $5 a month, or $50 a year Up to 50 aircraft on either.
Look round a real shop first Start free
The demonstration shop is eleven real aircraft with a year of work behind them. No account needed.
The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1