AD 98-09-07
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Fokker Services | F27 Mark 100 | Airworthiness Directives; Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 Series Airplanes |
| aircraft | Fokker Services | F27 Mark 200 | Airworthiness Directives; Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 Series Airplanes |
| aircraft | Fokker Services | F27 Mark 300 | Airworthiness Directives; Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 Series Airplanes |
| aircraft | Fokker Services | F27 Mark 400 | Airworthiness Directives; Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 Series Airplanes |
| aircraft | Fokker Services | F27 Mark 500 | Airworthiness Directives; Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 Series Airplanes |
| aircraft | Fokker Services | F27 Mark 600 | Airworthiness Directives; Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 Series Airplanes |
| aircraft | Fokker Services | F27 Mark 700 | Airworthiness Directives; Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 Series Airplanes |
Unsafe Condition
Fatigue cracking in the lapjoint below the chine line at certain fuselage stations, which could result in reduced structural integrity of the fuselage.
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Required Actions
Modify the lapjoint below the chine line between specified fuselage stations in accordance with Part 1, 2, or 3 of Fokker Service Bulletin F27/53-116, depending on prior service history. Accomplishment of these modifications terminates certain repetitive inspection requirements under AD 96-13-07.
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Compliance Time
Prior to the accumulation of 32,000 total flight cycles, or within 2 years after the effective date of this AD, whichever occurs later (for paragraphs (a) and (b)); prior to 56,000 total flight cycles or within 2 years after the effective date for paragraph (c).
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Affected Aircraft
Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 series airplanes, serial numbers 10102 through 10375 inclusive, operated or operated at a maximum cabin pressure differential of 5.5 psi.
AI-generated summary from the source AD text. Verify against the official source before acting.
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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