Commonwealth legislation

AD/CESSNA 190/2 Amdt 3 - Fuselage Front and Rear Spars

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This airworthiness directive (AD/CESSNA 190/2, Amdt 3) requires Cessna 190/195 owners/operators to modify the fuselage centre front spar per Cessna SL 63-40 and to carry out recurring dye‑penetrant and visual inspections and bolt/bushing checks of front and rear spars; defective parts must be replaced or repaired to an approved drawing (Requirement paras 1–3; Compliance). Owners/operators pay for and schedule the modification, inspections and any replacements, creating recurring maintenance obligations and potential aircraft downtime under the specified intervals (Compliance).

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AD/CESSNA 190/2 Amdt 3 - Fuselage Front and Rear Spars

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COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY

SCHEDULE OF AIRWORTHINESS DIRECTIVES

View image in the official source Cessna 190 and 195 Series Aeroplanes

AD/CESSNA 190/2

Amdt 3

Applicability: All models.

Fuselage Front and Rear Spars 11/67

Requirement: 1. Modification: Modify the fuselage centre section front spar in accordance with Cessna SL 63-40.

2. Inspection:

(a) Carry out a dye-penetrant inspection for cracking of the fuselage centre section front spar lower cap and steel reinforcing bars in the region of the two inboard bolts at both sides of the fuselage.

(b) Carry out a dye-penetrant inspection for cracking of the front spar side plates P/N 0311108 in the region of the steel reinforcing bars and in all accessible areas below the reinforcing bars.

(c) Carry out visual inspection for cracking, loose rivets or bolts or other signs of structural distress in the fuselage structure surrounding the front spar attachments. Pay particular attention to the front door post in the region immediately below the front spar side plates.

(d) Carry out a dye-penetrant inspection for cracking of the fuselage centre section rear spar, in the areas adjacent to both sides of the fuselage. Pay particular attention to the steel wing attachment plates and to the lower spar cap at the inboard ends of these plates.

(e) Remove the rear spar wing/fuselage attachment bolts and check the bolts, holes and eccentric bushings for cracks, wear or hole elongation, using the procedures and wear limitations specified in Cessna SL 190/195-1.

3. Any parts found defective during the above inspections shall be replaced with new parts or repaired to an approved drawing before further flight.

Compliance: 1. Modification, paragraph 1 - Forthwith.

Inspection:

For para. 2(a), (b) and (c) - at intervals not exceeding 300 hours time in service.

For para. 2(d) - before 4,500 hours total in service and thereafter at intervals not exceeding 300 hours time in service.

For para. 2(e) - at intervals not exceeding 600 hours time in service.

Source text

Sourced from the Federal Register of Legislation (legislation.gov.au), CC BY 4.0.