AD 2006-21-12 Airworthiness Directives; AeroSpace Technologies of Australia Pty Ltd. Models N22B, N22S, and N24A Airplanes

Models named: N22B, N22S, N24A. Read the applicability below — it usually turns on serial or part numbers too.

This AD affects Models N22B, N22S, and N24A airplanes, all serial numbers including airplanes with float/amphibian configuration, that are certificated in any category.

To address this problem, you must do the following:   Actions Compliance Procedures (1) Visually inspect the left-hand and right-hand ailerons for damage (i.e., distortion, bending, impact marks). Repair or replace any damaged aileron found (i) For Models N22B and N24A airplanes (airplanes previously affected by AD 2003-22-13): Inspect within the next 50 hours time-in-service (TIS) after December 23, 2003 (the effective date of AD 2003-22-13), unless already done Following the applicable maintenance manual.   (ii) For Model N22S airplanes (airplanes not previously affected by AD 2003-22-13): Inspect within the next 10 hours TIS or 30 days, whichever occurs first, after the effective date of this AD, unless already done   (iii) For all affected airplanes: Repair or replace before further flight after the inspection (2) Adjust the engine power lever actuated landing gear “up” aural warning microswitches and then perform a ground test. If deficiencies are detected during the ground test, make the necessary adjustments (i) For Models N22B and N24A airplanes (airplanes previously affected by AD 2003-22-13): Within the next 50 hours TIS after December 23, 2003 (the effective date of AD 2003-22-13), unless already done following Nomad Alert Service Bulletin ANMD-57-18, dated December 19, 2002 Following Nomad Alert Service Bulletin ANMD-57-18, Rev 1, dated August 14, 2006, and the applicable maintenance manual.   (ii) For Model N22S airplanes (airplanes not previously affected by AD 2003-22-13): Within the next 10 hours TIS or 30 days, whichever occurs first, after the effective date of this AD, unless already done (3) For Model N22B airplanes: (i) Fabricate placards that incorporate the following words (using at least 1/8 -inch letters) and install these placards on the instrument panel within the pilot's clear view: (A) “RECOMMENDED APPROACH FLAPS 10 OR 20 DEG AT 90 KIAS”; (B) “USE 10° OR 20° FLAP FOR TAKE-OFF AND LANDING—WARNING—DO NOT EXCEED 20° FLAP EXTENSION DURING FLIGHT, LANDING GEAR UP WARNING WILL INITIATE FOR A TORQUE PRESSURE OF LESS THAN 30 PSI”; and (ii) Incorporate the following information into the Limitations section of the Airplane Flight Manual (AFM): (A) Limit the maximum flap extension to 20 degrees; and (B) Limit flaps down operations for landing to 10° or 20° flap. Within the next 50 hours TIS after December 23, 2003 (the effective date of AD 2003-22-13), unless already done following Nomad Alert Service Bulletin ANMD-57-18, dated December 19, 2002 Following Nomad Alert Service Bulletin ANMD-57-18, Rev 1, dated August 14, 2006. To show compliance with paragraphs (e)(3)(ii)(A) and (e)(3)(ii)(B) of this AD, a copy of this AD may be inserted into the Limitations section of the AFM. 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 do the AFM insertion and the placard requirements of paragraphs (e)(3)(i)(A) and (e)(3)(i)(B) of this AD. Make an entry into the aircraft records showing compliance with these portions of the AD following section 43.9 of the Federal Aviation Regulations (14 CFR 43.9). (4) For Model N22S airplanes: (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: “USE 10° FLAP FOR TAKE-OFF AND LANDING—WARNING—DO NOT EXCEED 10° FLAP EXTENSION DURING FLIGHT, LANDING GEAR UP WARNING WILL INITIATE FOR A TORQUE PRESSURE OF LESS THAN 30 PSI”; and (ii) Incorporate the following information into the Limitations section of the AFM: (A) Limit the maximum flap extension to 10 degrees; and (B) Limit flaps down operations for landing to 10° flap. Within the next 10 hours TIS or 30 days, whichever occurs first, after the effective date of this AD, unless already done Following Nomad Alert Service Bulletin ANMD-57-18, Rev 1, dated August 14, 2006. To show compliance with paragraphs (e)(4)(ii)(A) and (e)(4)(ii)(B) of this AD, a copy of this AD may be inserted into the Limitations section of the AFM. 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 do the AFM insertion and the placard requirement of paragraph (e)(4)(i) of this AD. Make an entry into the aircraft records showing compliance with these portions of the AD following section 43.9 of the Federal Aviation Regulations (14 CFR 43.9). (5) For Model N24A airplanes: (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: “USE 10° FLAP FOR TAKE-OFF AND LANDING—WARNING—DO NOT EXCEED 10° FLAP EXTENSION DURING FLIGHT, LANDING GEAR UP WARNING WILL INITIATE FOR A TORQUE PRESSURE OF LESS THAN 30 PSI”; and (ii) Incorporate the following information into the Limitations section of the AFM: (A) Limit the maximum flap extension to 10 degrees; and (B) Limit flaps down operations for landing to 10° flap. Within the next 50 hours TIS after December 23, 2003 (the effective date of AD 2003-22-13), unless already done following Nomad Alert Service Bulletin ANMD-57-18, dated December 19, 2002 Following Nomad Alert Service Bulletin ANMD-57-18, Rev 1, dated August 14, 2006. To show compliance with paragraphs (e)(5)(ii)(A) and (e)(5)(ii)(B) of this AD, a copy of this AD may be inserted into the Limitations section of the AFM. 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 do the AFM insertion and the placard requirement of paragraph (e)(5)(i) of this AD. Make an entry into the aircraft records showing compliance with these portions of the AD following section 43.9 of the Federal Aviation Regulations (14 CFR 43.9). Alternative Methods of Compliance (AMOCs) (f) The Manager, Standards Staff, FAA, ATTN: Doug Rudolph, Aerospace Engineer, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4059; fax: (816) 329-4090, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (g) AMOCs approved for AD 2003-22-13 are not approved for this AD. Related Information (h) This AD relates to Australian AD/GAF-N22/69, Amendment 5, dated September 14, 2006, which references Nomad Alert Service Bulletin ANMD-57-18, Rev 1, dated August 14, 2006. Material Incorporated by Reference (i) You must use Nomad Alert Service Bulletin ANMD-57-18, Rev 1, dated August 14, 2006, 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 this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Nomad Operations, Aerospace Support Division, Boeing Australia, PO Box 767, Brisbane, QLD 4000 Australia; telephone 61 7 3306 3366; fax 61 7 3306 3111. (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, 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/code_of_federal_regulations/ibr_locations.html. Issued in Kansas City, Missouri, on October 13, 2006. James E. Jackson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-17425 Filed 10-18-06; 8:45 am] BILLING CODE 4910-13-P

This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Australia. We are issuing this AD to prevent failure of the aileron due to undetected pre-existing aileron damage and airplane operation outside of the approved limits. Aileron failure could lead to reduced or loss of control of the airplane.