Airworthiness Directive · Amendment 39-15482 · Wings
APEX Aircraft Model CAP 10B Airplanes
This AD applies to Model CAP 10B airplanes, serial numbers (SNs) 01, 02, 03, 04, and 1 through 282, certificated in any category, that have not been fitted with a replacement wood/carbon wing following application of major change 000302.
We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:
Unless already done, do the following actions:
(1) For Model CAP 10B airplanes with SNs 01, 02, 03, 04, and 1 through 263, within the next 100 hours time-in-service (TIS) after July 23, 1993 (the compliance date retained from AD 2003-04-02), unless already done, install a permanent inspection opening in the No. 1 wing rib following Avions Mudry Service Bulletin CAP10B No. 16, dated April 27, 1992. Inspection openings are incorporated during production for airplanes having a serial number of 264 or higher.
(2) For all affected airplanes, initially inspect the upper wing spar cap, the main wing spar undersurface, and the landing gear attachment blocks for cracks within the next 55 hours TIS after April 4, 2003 (the compliance date retained from AD 2003-04-02) following APEX Aircraft Document No. 1000913GB, dated February 4, 2002; APEX Aircraft Document No. 1000914GB, dated February 4, 2002; and APEX Aircraft Document No. 1000915GB, dated February 4, 2002. Repetitively inspect the upper wing spar cap and the main wing spar undersurface thereafter at intervals not to exceed 55 hours TIS. Repetitively inspect the landing gear attachment blocks thereafter at intervals not to exceed 1,000 hours TIS.
(3) For all affected airplanes, before further flight if any cracks are found during any inspection required in paragraph (f)(2) of this AD, do the following:
(i) Obtain a repair scheme from the manufacturer through the FAA at the address specified in paragraph (h)(1) of this AD;
(ii) Incorporate this repair scheme; and
(iii) Continue to inspect as specified in paragraph (f)(2) of this AD.
(4) For all affected airplanes, unless already done, do the following actions:
(i) Load factors limitation: Before further flight, as of May 27, 2008 (the effective date of this AD), the load factors limitation for solo flight is +5 and −3.5 Gs and when 2 persons are on board is +4.3 and −3.5 Gs.
(ii) Flick (snap roll) maneuvers speed limitation: Before further flight, as of May 27, 2008 (the effective date of this AD), for positive and negative flick maneuvers, the airspeed limitation is 160 km/hour (86 knots).
(5) For all affected airplanes, before further flight after May 27, 2008 (the effective date of this AD), fabricate a placard:
(i) Incorporate the following words (using at least 1/8 -inch letters) in the placard and install this placard on the instrument panel within the pilot's clear view: “THE NEVER EXCEED AIRSPEED FOR POSITIVE OR NEGATIVE FLICK MANEUVERS IS 160 KM/H (86 KNOTS). THE LOAD FACTORS LIMITATION FOR SOLO FLIGHT IS +5 AND −3.5 Gs AND WHEN 2 PERSONS ARE ON BOARD IS +4.3 AND −3.5 Gs.”
(ii) The owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7) may fabricate the placard required in paragraph (g)(3)(i) of this AD. Make an entry into the aircraft records showing compliance with this portion of the AD in accordance with section 43.9 of the Federal Aviation Regulations (14 CFR 43.9).
Note: This AD differs from the MCAI and/or service information as follows: This AD does not include the requirement from the MCAI to route the request to operate beyond the load factors limitation and flick (snap roll) maneuvers speed limitation through the Direction Générale de L'Aviation Civile (DGAC). You may make this request to the FAA following paragraph (h)(1) of this AD.
