Airworthiness Directive · Amendment 39-15038 · Wings
APEX Aircraft (Type Certificate No. A36EU Formerly Held by AVIONS MUDRY et CIE) Model CAP 10 B Airplanes
This AD applies to Model CAP 10 B airplanes, all serial numbers, that are:
(1) Certificated in any category; and
(2) fitted with major change 000302, wood/carbon-made wings, part-number 11.56.00.010, serial numbers 001 to 084 inclusive.
We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by the 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) Before further flight after May 21, 2007 (the effective date of this AD):
(i) Fabricate a placard that incorporates the following words (using at least 1/8 -inch letters) and install this placard on the instrument panel within the pilot's clear view: “FLICK MANEUVERS ARE PROHIBITED”; and
(ii) Insert a copy of this AD into the Limitations section of the Pilot's Operating Handbook (POH).
(iii) 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 (f)(1)(i) of this AD and may insert the information into the POH as required in paragraph (f)(1)(ii) of this AD. Make an entry into the aircraft records showing compliance with these portions of the AD in accordance with section 43.9 of the Federal Aviation Regulations (14 CFR 43.9).
(2) Within the next 50 hours time-in-service (TIS) after May 21, 2007 (the effective date of this AD), inspect the front and rear spar webs for cracks and damage using Apex Aircraft Service Bulletin No. 060307 R1, Amendment date November 2, 2006.
(3) If any crack or damage is found during the inspection required in paragraph (f)(2) of this AD, the wing must be considered as unairworthy until the implementation of the relevant repair solution. Before further flight, contact Apex Aircraft to obtain a repair solution and incorporate the repair. Continued operation with cracks in the front and rear spar webs is prohibited.
(4) If no cracks or damages are found in either the rear or the front wing spar web during the inspection required in paragraph (f)(2) of this AD, before further flight install reinforcement plates, part number 97.56.00.002, using Apex Aircraft CAP10C—Main Spar Wooden Center Block—Reinforcement Instructions No. 1001766-A, dated June 10, 2006; and Apex Aircraft Document No. 1001133-A, DR400 Spar Consolidation, Applying Araldite 2015 Adhesive, dated February 4, 2003.
(5) After doing the actions required in paragraphs (f)(2), (f)(3), and (f)(4) of this AD:
(i) Flick maneuvers previously prohibited by paragraph (f)(1) of this AD are now permitted. Before further flight, remove the placard required in paragraph (f)(1)(i) of this AD and remove the insertion into the POH required in paragraph (f)(1)(ii) of this AD.
(ii) Repetitively inspect the front and rear spar webs for cracks and damage thereafter at intervals not to exceed 13 months using Apex Aircraft Service Bulletin No. 060307 R1, Amendment date November 2, 2006; and
(iii) If any crack or damage is found during any inspection required by paragraph (f)(5)(ii) this AD, before further flight contact Apex Aircraft to obtain a repair solution and incorporate the repair.
(6) After 50 hours TIS after May 21, 2007 (the effective date of this AD), do not install an Apex Aircraft wood/carbon-made wing, part number 11.56.00.010, unless it has been inspected and is found to be crack free and modified using Apex Aircraft Service Bulletin No. 060307 R1, Amendment date November 2, 2006; and Apex Aircraft CAP10C—Main Spar Wooden Center Block—Reinforcement Instructions No. 1001766-A, dated October 6, 2006.
Note: This AD differs from the MCAI and/or service information as follows: The MCAI allows continued flight if cracks are found in the wing spar webs that do not exceed certain limits. The applicable service bulletin specifies replacing the wing spar webs only if cracks are found exceeding limits specified in Apex Aircraft Service Bulletin No. 060307 R1, Amendment date November 2, 2006, as does the MCAI. This AD does not allow continued flight if any crack is found. FAA policy is to disallow airplane operation when known cracks exist in primary structure, unless the ability to sustain ultimate load with these cracks is proven. The wing spar webs are considered primary structure, and the FAA has not received any analysis to prove that ultimate load can be sustained with cracks in these areas.
