AD 2008-17-06 Airworthiness Directives; Bombardier Model DHC-8-400 Series Airplanes

Models named: DHC-8-400, DHC-8-401, DHC-8-402. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Bombardier Model DHC-8-400, DHC-8-401, and DHC-8-402 airplanes, certificated in any category; serial numbers 4001 and 4003 and subsequent.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Requirements of AD 2007-12-03 Airplane Flight Manual (AFM) Revision (f) Within 14 days after July 10, 2007 (the effective date of AD 2007-12-03), revise the Limitations section of the applicable AFM to include the information in the applicable Bombardier temporary amendment specified in Table 1 of this AD, as specified in the temporary amendment. These temporary amendments introduce procedures for pulling the “HYD PWR XFER” circuit breaker in the event of the loss of all hydraulic fluid in the No. 1 or No. 2 hydraulic system. Operate the airplane according to the limitations and procedures in the applicable temporary amendment. Table 1—AFM Temporary Amendments For model— Use Bombardier temporary amendment— Issue— Dated— To Bombardier Dash 8 Q400 airplane flight manual— DHC-8-400 airplanes 13 1 July 14, 2005 PSM 1-84-1A. DHC-8-401 airplanes 13 1 July 14, 2005 PSM 1-84-1A. DHC-8-402 airplanes 13 1 July 14, 2005 PSM 1-84-1A. Note 1: This may be done by inserting a copy of the applicable temporary amendment into the applicable AFM. When the applicable temporary amendment has been included in general revisions of the AFM, the general revisions may be inserted into the AFM, provided the relevant information in the general revisions is identical to that in the temporary amendment. New Requirements of This AD AFM Revision (g) Within 14 days after the effective date of this AD, revise the applicable AFM Normal and Abnormal Procedures section to include the information in the applicable Bombardier temporary amendment specified in Table 2 of this AD, as specified in the temporary amendment. These temporary amendments introduce additional procedures for ensuring that the “PTU CNTRL” switch is Normal, the “PTU CNTRL ON” advisory light is out, and the “HYD PWR XFER” circuit breaker is pulled in the event of the illumination of the “#2 HYD ISO VALVE” caution light. After accomplishing the AFM revision, the AFM limitation required by paragraph (f) in this AD may be removed from the AFM. Table 2—AFM Temporary Amendments For model— Use Bombardier temporary amendment— Issue— Dated— To Bombardier Dash 8 Q400 airplane flight manual— DHC-8-400 airplanes 13 3 June 9, 2008 PSM 1-84-1A. DHC-8-401 airplanes 13 3 June 9, 2008 PSM 1-84-1A. DHC-8-402 airplanes 13 3 June 9, 2008 PSM 1-84-1A. Alternative Methods of Compliance (AMOCs) (h) The Manager, New York Aircraft Certification Office, ANE-170, 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: Fabio Buttitta, Aerospace Engineer, Systems and Flight Test Branch, ANE-172, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228-7303; fax (516) 794-5531. 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. Related Information (i) Canadian airworthiness directive CF-2006-08, dated April 26, 2006, also addresses the subject of this AD. Material Incorporated by Reference (j) You must use the applicable temporary amendment identified in Table 3 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. (Only the last pages of the temporary amendments identified in Table 4 of this AD contain the issue date, no other pages of those documents are dated.) Table 3—All Material Incorporated by Reference Bombardier temporary amendment— Issue— Dated— To Bombardier Dash 8 Q400 airplane flight manual— 13 1 July 14, 2005 Model 400 PSM 1-84-1A. 13 1 July 14, 2005 Model 401 PSM 1-84-1A. 13 1 July 14, 2005 Model 402 PSM 1-84-1A. 13 3 June 9, 2008 Model 400 PSM 1-84-1A. 13 3 June 9, 2008 Model 401 PSM 1-84-1A. 13 3 June 9, 2008 Model 402 PSM 1-84-1A. (1) The Director of the Federal Register approved the incorporation by reference of the temporary amendments identified in Table 4 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.  Table 4—New Material Incorporated by Reference Bombardier temporary amendment— Issue— Dated— To Bombardier Dash 8 Q400 airplane flight manual— 13 3 June 9, 2008 Model 400 PSM 1-84-1A. 13 3 June 9, 2008 Model 401 PSM 1-84-1A. 13 3 June 9, 2008 Model 402 PSM 1-84-1A. (2) On July 10, 2007 (72 FR 30968, June 5, 2007), the Director of the Federal Register approved the incorporation by reference of the temporary amendments identified in Table 5 of this AD.  Table 5—Previously Approved Material Incorporated by Reference Bombardier temporary amendment— Issue— Dated— To Bombardier Dash 8 Q400 airplane flight manual— 13 1 July 14, 2005 Model 400 PSM 1-84-1A. 13 1 July 14, 2005 Model 401 PSM 1-84-1A. 13 1 July 14, 2005 Model 402 PSM 1-84-1A. (3) Contact Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada, for a copy of this service information. You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; 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 Renton, Washington, on July 31, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8-18683 Filed 8-14-08; 8:45 am] BILLING CODE 4910-13-P

This AD results from low No. 2 hydraulic pressure in-flight, which caused the power transfer unit to overspeed, and the fluid flow within the No. 1 hydraulic system to increase. We are issuing this AD to prevent possible loss of both the No. 1 and No. 2 hydraulic systems, resulting in the potential loss of several functions essential for safe flight and landing of the airplane.