What is the payload capacity threshold for a turbine-powered large aeroplane to be subject to the repair approval requirements in AMC1 21.A.433(a)(5)?

The payload capacity threshold is 3 402 kg (7 500 lbs) or more.

Which regulation point does AMC1 21.A.433(a)(5) provide acceptable means of compliance for?

It provides acceptable means of compliance for point 21.A.433(a)(5), which concerns requirements for the approval of repairs to large aeroplanes subject to point 26.302 of Part-26.

In the context of AMC1 21.A.433(a)(5), what is the role of 'specifications used for compliance with the applicable points of Part-26'?

They serve as an alternative certification basis for the repair when the aeroplane's original certification basis precedes JAR 25.571 Change 7 or 14 CFR §25.571 Amendment 45, specifically for the fatigue-critical structures affected by the repair.

AMC1 21.A.433(a)(5) Requirements for the approval of repairs to large aeroplanes subject to point 26.302 of Part-26

Q: What are the two acceptable certification bases for a repair affecting fatigue-critical structures on a large turbine-powered aeroplane, according to AMC1 21.A.433(a)(5)?

The certification basis used for the repair must be either (a) Amdt 19 to CS 25.571 or subsequent amendments, or (b) the certification basis of the aeroplane, unless that basis precedes JAR 25.571 Change 7 or 14 CFR §25.571 Amendment 45, in which case the certification basis must be either JAR 25.571 Change 7 or 14 CFR §25.571 Amendment 45 (or later amendments), or the specifications used for compliance with the applicable points of Part-26 for the affected fatigue-critical structures.

Q: For which types of aeroplanes does AMC1 21.A.433(a)(5) apply when assessing repairs to fatigue-critical structures?

It applies to repairs that affect fatigue-critical structures of turbine-powered large aeroplanes certified to carry 30 passengers or more, or with a payload capacity of 3 402 kg (7 500 lbs) or more.

Q: If an aeroplane's original certification basis predates JAR 25.571 Change 7 and 14 CFR §25.571 Amendment 45, what options are available for the certification basis of a repair under AMC1 21.A.433(a)(5)?

The certification basis for the repair should be either (1) JAR 25.571 Change 7 or 14 CFR §25.571 Amendment 45, or later amendments, or (2) the specifications used for compliance with the applicable points of Part-26 for the fatigue-critical structures affected by the repair.

Q: According to AMC1 21.A.433(a)(5), what does a damage-tolerance evaluation demonstrate when the certification basis for a repair is Amdt 19 to CS 25.571 or later?

The damage-tolerance evaluation demonstrates compliance with point 21.A.433(a)(5) when the certification basis used for the repair is Amdt 19 to CS 25.571 or subsequent amendments.

Q: Under AMC1 21.A.433(a)(5), if the aeroplane's certification basis is older than JAR 25.571 Change 7, can the repair use the original certification basis directly?

No, if the certification basis precedes JAR 25.571 Change 7 or 14 CFR §25.571 Amendment 45, the certification basis for the repair should be either JAR 25.571 Change 7 or 14 CFR §25.571 Amendment 45 (or later amendments), or the specifications used for compliance with the applicable points of Part-26 for the affected fatigue-critical structures.

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AMC1 21.A.433(a)(5) Requirements for the approval of repairs to large aeroplanes subject to point 26.302 of Part-26

ED Decision 2021/007/R

For repairs that affect fatigue-critical structures of turbine-powered large aeroplanes certified to carry 30 passengers or more, or with a payload capacity of 3 402 kg (7 500 lbs) or more, damage-tolerance evaluations demonstrate compliance with point 21.A.433(a)(5) when the certification basis used for the repair is:

(a) Amdt 19 to CS 25.571, or subsequent amendments; or

(b) the certification basis of the aeroplane, unless it precedes JAR 25.571 Change 7 or 14 CFR §25.571 Amendment 45, in which case the certification basis for the repair should be:

(1) JAR 25.571 Change 7 or 14 CFR §25.571 Amendment 45, or later amendments; or

(2) the specifications used for compliance with the applicable points of Part‑s26 for the fatigue-critical structures affected by the repair.

Details

Source-Title: AMC1 21.A.433(a)(5) Requirements for the approval of repairs to large aeroplanes subject to point 26.302 of Part-26 View latest amendments

Erulesid: ERULES-1963177438-18972 Compare versions

Domain: Initial airworthiness

Applicabilitydate: 29 May, 2021

Entryintoforcedate: 29 May, 2021

Regulatorysource: ED Decision 2021/007/R Navigate

Regulatorysubject: Part-21

Typeofcontent: AMC to IR (Acceptable means of compliance to implementing rule)

Origin: EASA

Category: EAR