AircraftDirectives
MembershipSign inCreate free account
Menu
Airworthiness Directive

AD 99-24-09 64 FR 66365 Active

Federal Aviation Administration · 14 CFR part 39

Requires modifying the flap inboard attachment fittings through the installation of a reinforcement angle bracket on the inside of the center web of both flap inner attachment fittings.

Federal Register (opens in a new tab)FAA DRS (opens in a new tab)

FR document
99-30520
Amendment
39-11433
Published
1999-11-26
Effective
2000-01-14
Models covered
1

Last live check: 2026-08-19

Printed from https://aircraftdirectives.com/ad/99-24-09 · AircraftDirectives restates official FAA and manufacturer records; the official sources named on this sheet control. Not an airworthiness determination.

This page is a reference Record, not an airworthiness or compliance determination. Official FAA and manufacturer sources control over our restatement, subject to governing law. Check applicability, current requirements and incorporated documents before acting. The owner or operator remains responsible for airworthiness and required records under 14 CFR 91.403 and 91.417, as applicable. Terms of Use: /terms.

Opens your browser's print dialog. Choose “Save as PDF” to export a file. Keyboard: Ctrl+P or Cmd+P.

AD

99-24-09

FR doc 99-30520 · 64 FR 66365

AD 99-24-09Published 1999-11-26Effective 2000-01-14

FAA rule - 14 CFR 39

FAA rule. Compliance with an applicable AD is required under 14 CFR 39.7. Check its effective date, applicability, compliance times and current status.

Requires modifying the flap inboard attachment fittings through the installation of a reinforcement angle bracket on the inside of the center web of both flap inner attachment fittings.

Full official abstract

This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC- 12/45 airplanes. This AD requires modifying the flap inboard attachment fittings through the installation of a reinforcement angle bracket on the inside of the center web of both flap inner attachment fittings. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to prevent the potential of the inboard flap attachment fittings buckling while operating at full flaps with full power into a head-on wind gust, which could result in loss of control of the airplane.

More directives for Pilatus PC-12

  1. AD 2026-15-12 Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes Effective 2026-10-02
  2. AD 2026-15-07 Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes Effective 2026-09-03
  3. AD 2026-12-01 Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes Effective 2026-07-14
  4. AD 2026-08-11 Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes Effective 2026-05-11
  5. AD 2024-08-07 Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes Effective 2024-06-03

All Pilatus PC-12 directives

View on Federal Register (opens in a new tab) View this AD in FAA DRS (opens in a new tab) Print AD packet (opens the full Federal Register document in a new tab)

Applies to 1 model in our index