EFFECTIVE DATE

(a) This airworthiness directive (AD) becomes effective May 27, 2008.

AFFECTED ADS

(b) This AD supersedes AD 2003-04-02, Amendment 39-13050.

APPLICABILITY

(c) 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.

SUBJECT

(d) Air Transport Association of America (ATA) Code 57: Wings.

REASON

(e) The mandatory continuing airworthiness information (MCAI) states:

    Further to a new  fracture in flight of  a CAP 10B wing  in June 2003,
    the  investigation  in  process  seems  to  point  out  that  a  wrong
    application of CAP 10B Service Bulletin No. 16 (CAP 10B-57-004)  would
    lead to the impossibility of detecting the potential spar damage while
    performing the Type Certificate holder upper spar flange inspection.

    The  MCAI requires  you to  check that  the No.  1 wing  rib has  been
    modified, comply with load  factors and operating limitations,  and do
    repetitive inspections of the upper and lower spar flanges and landing
    gear attachment blocks.

ACTIONS AND COMPLIANCE

(f) 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).

FAA AD DIFFERENCES

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  Generale  de
L'Aviation Civile (DGAC).  You may  make this request to the FAA following
paragraph (h)(1) of this AD.

OTHER FAA AD PROVISIONS

(h) The following provisions also apply to this AD:

(1) Alternative  Methods  of Compliance  (AMOCs): The  Manager,  Standards
    Office,  FAA,  has  the authority  to approve  AMOCs for  this AD,  if
    requested using the procedures found in 14 CFR 39.19. Send information
    to ATTN: Sarjapur Nagarajan,  Aerospace Engineer, FAA, Small  Airplane
    Directorate,  901  Locust,  Room  301,  Kansas  City,  Missouri 64106;
    telephone:  (816) 329-4145;  fax:  (816) 329-4090.  Before  using  any
    approved AMOC on any airplane  to which the AMOC applies,  notify your
    appropriate  principal  inspector  (PI) in  the  FAA  Flight Standards
    District Office (FSDO), or lacking a PI, your local FSDO.

(2) Airworthy Product: For any requirement in this AD to obtain corrective
    actions from a manufacturer or other source, use these actions if they
    are FAA-approved.  Corrective actions  are considered  FAA-approved if
    they are approved by the State of Design Authority (or their delegated
    agent). You are required to assure the product  is airworthy before it
    is returned to service.

(3) Reporting Requirements:  For  any  reporting requirement  in this  AD,
    under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et
    seq.), the  Office of  Management and  Budget (OMB)  has approved  the
    information  collection  requirements  and  has  assigned  OMB Control
    Number 2120-0056.

RELATED INFORMATION

(i) Refer  to MCAI  French AD  2003-375(A), dated  October 1, 2003; Avions
    Mudry & CIE  Service Bulletin CAP  10B No. 16,  dated April 27,  1992,
    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,  for related
    information.

MATERIAL INCORPORATED BY REFERENCE

(j) You must use Avions Mudry & CIE Service Bulletin CAP 10B No. 16, dated
    April 27, 1992; 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,  to
    do the actions required by this AD, unless the AD specifies otherwise.

(1) The  Director of  the Federal  Register approved  the incorporation by
    reference of 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,
    under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) On  July 23,  1993 (58  FR 31342,  June 2,  1993), the Director of the
    Federal Register previously approved the incorporation by reference of
    Avions Mudry & CIE  Service Bulletin CAP 10B  No. 16, dated April  27,
    1992.

(3) For service information identified in this AD, contact APEX  Aircraft,
    Bureau  de Navigabilite,  1, route  de Troyes,  21121  DAROIS--France;
    telephone:  +33  380  35  65  10;  fax  +33  380  35  65  15;  e-mail:
    airworthiness@apex-aircraft.com;       Internet:       http://www.apex
    -aircraft.com.

(4) You may  review copies  at  the  FAA, Central  Region, Office  of  the
    Regional Counsel, 901 Locust,  Room 506, Kansas City,  Missouri 64106;
    or at  the National  Archives and  Records Administration  (NARA). For
    information on  the availability  of this  material at  NARA, call 202
    -741-6030, or go to:
    http://www.archives.gov/federal-register/cfr/ibr-locations.html.

Issued in  Kansas City,  Missouri, on  April 11,  2008. James  E. Jackson,
Acting  Manager,  Small   Airplane  Directorate,  Aircraft   Certification
Service.

FOR FURTHER INFORMATION  CONTACT: Sarjapur Nagarajan,  Aerospace Engineer,
FAA,  Small  Airplane  Directorate, 901  Locust,  Room  301, Kansas  City,
Missouri 64106; telephone: (816) 329-4145; fax: (816) 329-4090.