(b)
For metallic components, compliance with paragraph (a) of this section may be shown by–

(1)
Electrically bonding the components properly to the airframe; or

(2)
Designing the components so that a strike will not endanger the rotorcraft.

(c)
For nonmetallic components, compliance withparagraph(a) ofthis section may be shown by–

(1)
Designing the components to minimize the e.ect of a strike; or

(2)
Incorporating acceptable means of diverting the resulting electrical current to not endanger the rotorcraft.

(d)
[The electric bondingand protection against lightning and static electricity must–

(1)
Minimize the accumulation of electrostatic charge;

(2)
Minimize the risk of electric shock to crew, passengers, and service and main-tenance personnel using normal precautions;

(3)
Provide an electrical return path, under both normal and fault conditions, on rotorcraft having grounded electrical systems; and

(4)
Reduce to an acceptable level the e.ects of lightning and static electricity on the functioning of essential electrical and electronic equipment.]

Amdt. 29-40, E.. 8/8/96
FAR 29.611 : Inspection provisions.
There must be means to allow close examination of each part that requires–
(a)
Recurring inspection;

(b)
Adjustmentforproper alignment andfunctioning; or

(c)
Lubrication.

′
Elodie Roux. Septembre 2003
Subpart D : Design and Construction
FAR 29.613 : Material strength properties and design values.
(a)
Material strength properties must be based on enough tests of material meeting speci.cations to establish design values on a statistical basis.

(b)
[ Design values must be chosen to minimize the probability of structural failure dueto materialvariability.Exceptasprovidedinparagraphs(d) and(e) ofthis section, compliance with this paragraph must be shown by selecting design values that assure material strength withthefollowingprobability–

(1)
Where appliedloads are eventuallydistributedthrough a single member within an assembly, the failure of which would result in loss of structural integrity of the component,99percentprobability with95percent con.dence; and

(2)
For redundant structures, those in which the failure of individual elements would result in applied loads being safely distributed to other load-carrying members, 90 percent probability with 95 percent con.dence.]

(c)
The strength,detaildesign, andfabricationof the structure must minimizethepro-bability of disastrous fatigue failure, particularly at points of stress concentration.

(d)
[Design values maybethose containedinthefollowingpublications(availablefrom the Naval Publications and Forms Center, 5801 Tabor Avenue, Philadelphia, PA 19120) or other values approved by the Administrator :]

(1)
MIL-HDBK-5,”MetallicMaterialsandElementsforFlightVehicleStructure”.

(2)
MIL-HDBK-17, ”Plastics for Flight Vehicles”.

(3)
ANC-18, ”Design of Wood Aircraft Structures”.

(4)
MIL-HDBK-23, ”Composite Construction for Flight Vehicles”.

(e)
[Other design values may be used ifa selection of the material is made in which a specimen of each individual item is tested before use and it is determined that the actual strength properties of that particular item will equal or exceed those used in design.]

Amdt. 29-30, E.. 4/5/90
FAR 29.619 : Special factors.
(a)
The special factors prescribed in Secs. 29.621 through 29.625 apply to each part of the structure whose strength is–

(1)
Uncertain;

(2)
Likely to deteriorate in service before normal replacement; or
　
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