Under CS 29.337, what are the default positive and negative limit manoeuvring load factors?

The default positive limit manoeuvring load factor is 3.5 and the default negative limit is -1.0.

For a rotorcraft using the alternative load factor values under CS 29.337(b), what evidence is required to support the selected positive and negative limits?

The evidence required is that the probability of being exceeded is shown by analysis and flight tests to be extremely remote, and that the selected values are appropriate to each weight condition between the design maximum and design minimum weights.

What is the minimum positive limit manoeuvring load factor allowed under CS 29.337 if the default range is not used?

The minimum positive limit manoeuvring load factor allowed is 2.0.

What is the minimum negative limit manoeuvring load factor allowed under CS 29.337 if the default range is not used?

The minimum negative limit manoeuvring load factor allowed is -0.5.

What is the probability criterion for the alternative limit manoeuvring load factors under CS 29.337(b)?

The probability of being exceeded must be shown by analysis and flight tests to be extremely remote.

If a rotorcraft is designed with a positive limit manoeuvring load factor of 2.0 and a negative limit of -0.5, what must the manufacturer demonstrate regarding the probability of exceeding these values?

The manufacturer must demonstrate by analysis and flight tests that the probability of being exceeded is extremely remote.

What is the range of limit manoeuvring load factors specified in the default design condition of CS 29.337?

The range is from a positive limit of 3.5 to a negative limit of -1.0.

CS 29.337 Limit manoeuvring load factor

Q: What is the required positive limit manoeuvring load factor for a rotorcraft if the manufacturer does not choose the default range?

The positive limit manoeuvring load factor must be not less than 2.0, and the negative limit manoeuvring load factor must be not less than -0.5, provided the probability of being exceeded is shown by analysis and flight tests to be extremely remote, and the selected values are appropriate to each weight condition between the design maximum and design minimum weights.

Q: What two conditions must be met if a rotorcraft is designed with a positive limit manoeuvring load factor of 2.5 and a negative limit of -0.5?

The two conditions are: (1) the probability of being exceeded must be shown by analysis and flight tests to be extremely remote; and (2) the selected values must be appropriate to each weight condition between the design maximum and design minimum weights.

Q: Does CS 29.337 require that the selected alternative load factors be appropriate for all weight conditions?

Yes, the selected values must be appropriate to each weight condition between the design maximum and design minimum weights.

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CS 29.337 Limit manoeuvring load factor

ED Decision 2003/16/RM

The rotorcraft must be designed for –

(a) A limit manoeuvring load factor ranging from a positive limit of 3.5 to a negative limit of -1.0; or

(b) Any positive limit manoeuvring load factor not less than 2.0 and any negative limit manoeuvring load factor of not less than –0.5 for which:

(1) The probability of being exceeded is shown by analysis and flight tests to be extremely remote; and

(2) The selected values are appropriate to each weight condition between the design maximum and design minimum weights.

Details

Source-Title: CS 29.337 Limit manoeuvring load factor View latest amendments

Erulesid: ERULES-1963177438-5604 Compare versions

Domain: Initial airworthiness

Amendedby: Initial issue

Applicabilitydate: 14 November, 2003

Entryintoforcedate: 14 November, 2003

Regulatorysource: ED Decision 2003/16/RM Navigate

Regulatorysubject: CS-29

Typeofcontent: CS (Certification specification)

Origin: EASA

Category: EAR

CS 29.337 Limit manoeuvring load factor

Details

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