AD 84-13-03 R1 ACTIVE

84-13-03 R1 CANADAIR: Amendment 39-4882 as amended by Amendment 39-5083. Applies to Model CL-600-1A11 (CL-600) and Model CL-600-2A12 (CL-601) airplanes, certificated in all categories. Compliance required as indicated.

A. To detect possible fatigue cracks in the outboard flap vane support structure, accomplish the following inspections for cracks on each side of the aircraft within 200 landings after the effective date of this AD, unless already accomplished within the last 200 landings, and thereafter at intervals not to exceed 400 landings.

1. Visually inspect the following parts:

a. The flap vane support straps, P/N 600-10460-13 and -23, at the inboard and outboard ends of the outboard flap.

b. The lower skins on the outboard flap vanes with particular attention given to the spanwise direction at the mid-chord position and the chordwise direction adjacent to the vane attachment points.

c. The three vane main support fittings and two vane intermediate support fittings attached to the outboard flap vane.

P/N 600-14562-1 and -2 (FS 189)

P/N 600-14563-1 and -2 (FS 235)
Main Supports:
P/N 600-14564-1 and -2 (FS 280)
Intermediate Supports:
P/N 600-14588-1 and -2 (FS 209)
or
P/N 600-14586-1 and -2 (FS 209)
or
P/N K600-14502-5 and -6 (FS 209)

P/N 600-14589-1 and -2 (FS 254)
or
P/N 600-14585-1 and -2 (FS 254)
or
P/N K600-14502-7 and -8 (FS 254)

Particular attention should be given to the root of the attachment lugs.
d. The two intermediate support blades attached to the outboard flap leading edge structure.

P/N 600-10463-35 (FS 209)
or
P/N K600-14502-1 (FS 209)

P/N 600-10463-37 (FS 254)
or
P/N K600-14502-3 (FS 254)

2. Conduct an eddy current or dye-penetrant inspection of the following parts:
The three outboard flap vane main support blades which form an integral part of the outboard flap hinge fittings.

P/N 600-14543-1 and -2 (FS 189)

P/N 600-14546-1, -2, -3,

and -4 (FS 235)

P/N 600-14547-1 and -2 (FS 280)

This must be accomplished along the root radius at the bottom edge of the blade where it passes through the leading edge of the flap. To accomplish this inspection, it is necessary to remove the sealant from the root radius. Reseal after inspection.

B. Parts found cracked during inspection must be replaced with serviceable or new parts prior to further flight. After replacement, continue to inspect in accordance with paragraph A., above.

C. Alternate means of compliance, which provide an equivalent level of safety may be used when approved by the Manager, New York Aircraft Certification Office, FAA, New England Region.

D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and door modifications required by this AD.

E. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, New York Aircraft Certification Office, FAA, New England Region, may adjust the repetitive inspection intervals required by this AD.

This supersedes Amendment 39-4687 (48 FR 33245; July 21, 1983), AD 83-14-06, and telegraphic AD T83-20-51 issued September 30, 1983.

Amendment 39-4882 became effective June 27, 1984.

This Amendment 39-5083 becomes effective July 26, 1985.