A Supplier's Bad Bushing Technique Just Triggered an FAA Order on 29 A320-Family Jets
A narrow manufacturing slip, a fleet-wide order
The US Federal Aviation Administration has adopted a new airworthiness directive covering select Airbus A318, A319, A320 and A321 aircraft, requiring operators to inspect a specific structural fitting on the main landing gear after tool-mark damage was discovered in the bore of forward and aft lugs on landing gear support rib 5. The directive, AD 2026-18-03, became effective September 18, 2026, according to the Federal Register notice and reporting by Airways Magazine, which reviewed the FAA's rulemaking documents.
The FAA traces the defect to a "quality escape" on the production assembly line: a supplier used an improper bushing-removal technique while installing components onto the rib, leaving tool-mark damage inside the lug bores of the affected aircraft. That damage, left unaddressed, could act as a stress concentration point and accelerate fatigue cracking in a structure that carries significant loads every time the aircraft takes off, lands, and taxis.
Twenty-nine aircraft on the US registry fall within the AD's scope, identified by specific model variants and manufacturer serial numbers listed in the directive. The order does not name the operators, and NewsFellow has not independently identified which US carriers have affected tails in their fleets; airlines typically decline to comment on individual tail-number compliance work until inspections are complete.
What investigators found — and what remains open
According to the FAA's published rationale, the root of the problem sits in how a bushing was removed from the rib-5 attachment area during original assembly — a step that left mechanical tool marks inside the bore surfaces of both the forward and aft lugs. Those bores house the pins that connect the landing gear support structure to the airframe, a joint that sees repeated cyclic loading throughout an aircraft's life.
The FAA's concern, as stated in the directive, is that "fatigue damage could lead to structural failure and landing gear collapse" if the tool-mark damage is not identified and evaluated. That is a conditional, forward-looking safety finding — the FAA is acting to prevent a failure mode it has assessed as plausible, not describing an accident or an in-service structural failure that has already occurred. No collapse, incident or injury linked to this specific lug damage has been reported by the FAA, Airbus or any aviation safety body as of this writing.
The AD does not specify how the tool-mark damage was originally discovered — whether through a production audit, a supplier quality review, or an in-service finding — and NewsFellow was unable to independently confirm that detail from publicly available FAA or EASA documentation at time of writing. Airbus has not issued a public statement specific to this AD as of publication.
The inspection regime
The directive requires operators of the affected aircraft to conduct a detailed visual inspection of the lug bores on landing gear support rib 5. The compliance schedule is tied to whichever comes later: a model-specific aircraft age threshold, or 500 flight cycles/1,000 flight hours accumulated after the AD's September 18 effective date. Airlines must then repeat the inspection at intervals of 500 flight cycles or 1,000 flight hours, whichever occurs first, for as long as the aircraft remains in that configuration.
The FAA also outlines an optional terminating action: operators may perform an approved repair or modification that would end the repetitive inspection requirement altogether, though that option carries a materially higher upfront cost than the recurring visual checks.
On cost, the FAA's own regulatory evaluation — a standard part of any AD rulemaking, used to estimate the economic burden on US operators — puts the routine inspection at roughly $255 per aircraft, per check, totaling an estimated $7,395 across the 29-aircraft US fleet for a single inspection cycle. The optional terminating repair is estimated at up to $59,625 per aircraft, reflecting the more invasive nature of a structural modification compared with a visual check.
Part of a busier-than-usual week for FAA structural orders
This AD arrived alongside two other Airbus-family directives published in the same window. One covers A350-1041 pylon fasteners, where the FAA cited a possible programming error or improper cutting-tool maintenance that left some fastener installations beneath primary pylon structure without proper chamfers — a defect the agency says could reduce fatigue life if fasteners are seated incorrectly. That directive currently affects zero US-registered aircraft, since no US carrier operates the A350-1041 sub-variant named in the order, but it applies globally to the 53 manufacturer serial numbers Airbus identified. The other directive, covering ATR 42-500 cargo-compartment ventilation shut-off valves, similarly has no current US registrations but requires a maintenance-program change internationally.
Taken together, the three orders illustrate a pattern regulators and manufacturers have wrestled with across recent years: production-line quality escapes — errors introduced during original manufacturing rather than defects that emerge from wear in service — being caught late enough that they require fleet-wide inspection mandates rather than simple in-line rework. In the A320-family case, the FAA's own language crediting the damage to a supplier's assembly technique places the origin squarely in the manufacturing chain rather than operational wear.
How landing gear support rib 5 fits into the airframe
Main landing gear support rib 5 is part of the wing structure closest to the fuselage centerline on A320-family aircraft, where the landing gear attaches and transfers ground loads — the full weight of the aircraft on touchdown, braking loads, and taxi stresses — into the wing box. The lugs at issue sit at the pin joints connecting the landing gear leg assembly to that rib. Because every landing and every taxi movement cycles load through this joint, any flaw that reduces the material's fatigue resistance at that location is treated by regulators as a priority structural concern, even when, as here, no failure has actually occurred.
Tool marks — small gouges or scoring left in a metal surface by a tool used incorrectly during manufacturing or maintenance — are a well-understood failure initiation point in aerospace structures. A smooth bore distributes stress evenly around its circumference; a scored or marked one concentrates stress at the mark, which can accelerate the formation and growth of fatigue cracks under repeated loading far faster than an undamaged surface would experience. That is the underlying engineering logic behind the FAA's inspection mandate: catch any affected lug before repeated flight cycles turn a manufacturing blemish into a crack.
Why this AD, and not a bulletin, was necessary
Airbus, like other major manufacturers, routinely issues service bulletins recommending inspections or repairs. An FAA airworthiness directive is a stronger instrument: it is a legally enforceable rule under US federal aviation regulations, and US-registered aircraft cannot legally continue operating past the compliance deadlines without completing the required action or an FAA-approved alternative means of compliance. The FAA typically issues an AD when it determines an unsafe condition exists or is likely to exist or develop on products of the same type design — in this case, aircraft carrying rib-5 support structure built with the flagged bushing-removal technique.
The FAA's rulemaking process for ADs generally begins by referencing or adopting a corresponding EASA directive when the aircraft type is of European design, since Airbus is certificated by EASA as the state of design. NewsFellow was not able to confirm from available reporting whether a parallel EASA directive for this specific rib-5 lug issue was published before or alongside the FAA's September 18 action; readers should treat the sequencing between the two regulators as unconfirmed pending direct documentation review.
What happens next
Airlines with affected tails now have a defined compliance clock running from September 18. Given the relatively modest per-inspection cost — roughly $255 versus a repair option nearing $60,000 — most operators are expected to opt for the repetitive visual-inspection path rather than the one-time terminating repair, at least in the near term, though the FAA's cost estimate does not account for aircraft downtime, which airlines weigh separately in scheduling maintenance checks.
No flight restrictions, groundings or route cancellations have been reported in connection with this AD, and the FAA's own economic evaluation — treating the inspection as a routine, low-cost line-maintenance task — is consistent with an order intended to be absorbed into standard maintenance checks rather than one requiring aircraft to be pulled from service on an emergency basis.
NewsFellow will continue to monitor for any airline-specific compliance statements, for confirmation of a corresponding EASA directive, and for any updates should inspections reveal damage beyond what the FAA's initial evaluation anticipated. As with any active airworthiness directive, this reporting will be updated to reflect further findings; no cause of eventual structural failure has been alleged because none has occurred — the directive addresses a condition regulators judged capable of leading to one if left unaddressed.
How production-line defects typically surface
Quality escapes of this kind — where a manufacturing error passes through a supplier's own inspection process and is only caught later, sometimes years after the affected aircraft entered service — are not unique to this AD, and the aviation industry has built layered systems specifically to catch them before they become safety events. Type-certificate holders like Airbus operate ongoing production audits, and suppliers are contractually required to flag process deviations, but bushing removal is a manual, tool-dependent step that depends on technician training and tool condition at the specific work station involved, which is one reason these escapes are typically found through later engineering review or fleet sampling rather than caught in the original production inspection line.
Once a manufacturer identifies a potential fleet-wide manufacturing issue, the normal sequence is: internal engineering assessment, notification to the relevant type-certificate authority (EASA for Airbus), a proposed corrective action, and — if the authority agrees an unsafe condition exists — a directive making inspection mandatory rather than advisory. The FAA then typically mirrors the state-of-design authority's action for aircraft on the US registry. The 29 aircraft affected in the US represent a small fraction of the global A320-family fleet, which numbers in the thousands, underscoring that this issue traces to a specific, bounded manufacturing batch rather than a design-wide vulnerability.
Reading the AD in context, not in isolation
It's worth being precise about what this directive does and does not say. It does not allege that any A320-family aircraft has suffered landing gear failure connected to this defect. It does not name the supplier responsible for the flawed bushing-removal work, nor does the publicly available FAA text identify which manufacturing batch, date range, or Airbus final-assembly line produced the affected rib-5 structures — details that, if they exist in non-public FAA or Airbus engineering records, were not part of the material reviewed for this report. And it does not affect the broader A320neo or A320ceo fleet generally — only the specific manufacturer serial numbers listed in the directive's applicability section carry the flagged tool-mark risk.
What it does confirm is that the FAA judged the risk serious enough to mandate action, and that the fix — at least in its recurring-inspection form — is inexpensive and fast enough to fold into routine maintenance visits without pulling aircraft from service on short notice. That combination is a fairly ordinary outcome of the industry's continuous airworthiness surveillance system working as designed, rather than a sign of a wider or unresolved safety gap in the A320 family.