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2003-13-08 Goodrich Avionics Systems, Inc.: Amendment 39-13208; Docket No. 2003-CE-25-AD.
(a) What airplanes are affected by this AD? Any Goodrich TAWS8000 terrain awareness warning system (TAWS), part number (P/N) 805-18000-001, that incorporates hardware "Mod None", "Mod A", or "Mod B", that is installed in, but not limited to, the following airplanes that are certificated in any category. Airplanes that are not in this list and have the TAWS installed through field approval or other methods are still affected by this AD:
Company
Models
Cessna Aircraft Company
421, 500, 501, 525, 525A, 550, 551, 650, and S550.
DASSAULT AVIATION
Mystere-Falcon 20 series.
Gulfstream Aerospace LP
1125 Westwind Astra.
Raytheon Aircraft Company
100, 200, 300, 400A, and F90.
Sabreliner Corporation
NA-265.
The New Piper Aircraft Inc
PA-42-1000.
(b) Who must comply with this AD? Anyone who wishes to operate any airplane with one of the above referenced Goodrich TAWS installed must comply with this AD.
(c) What problem does this AD address? The actions specified by this AD are intended to prevent the loading of the baro set potentiometer, which could result in an unacceptable attitude error. Such a condition could cause the pilot to make flight decisions that put the airplane in unsafe flight conditions.
(d) What must I do to address this problem? To address this problem, you must accomplish the following actions:
Actions
Compliance
Procedures
(1) Inspect the TAWS8000 TAWS (part number 805-18000-001 that incorporates hardware Mod None , Mod A , or Mod B ) installation to determine if both the TAWS8000
TAWS and any other device are connected to the same baro set potentiometer.
Within the next 5 hours time-in-service (TIS) after July 21, 2003 (the effective date of this AD), unless already accomplished.
In accordance with Goodrich Avionics Systems, Inc. Service Memo SM #134, dated May 2, 2003, and the applicable installation manual.
(2) If both the TAWS8000 TAWS and any other device are connected to the same baro set potentiometer, then remove the TAWS8000 TAWS and cap and stow the connecting wires.
Before further flight after the inspection required in paragraph (d)(1) of this AD.
In accordance with Goodrich Avionics Systems, Inc. Service Memo SM #134, dated May 2, 2003, and the applicable installation manual.
(3) Do not install any TAWS8000 TAWS (part number 805-18000-001 that incorporates hardware Mod None , Mod A , or Mod B ).
As of July 21, 2003 (the effective date of this AD).
Not Applicable.
(e) Can I comply with this AD in any other way? To use an alternative method of compliance or adjust the compliance time, follow the procedures in 14 CFR 39.19. Send these requests to the Manager, Chicago Aircraft Certification Office (ACO). For information on any already approved alternative methods of compliance, contact Brenda S. Ocker, Aerospace Engineer, FAA, Chicago ACO, 2300 East DevonAvenue, Des Plaines, Illinois 60018; telephone: (847) 294-7126; facsimile: (847) 294-7834.
(f) Are any service bulletins incorporated into this AD by reference? Actions required by this AD must be done in accordance with Goodrich Avionics Systems, Inc. Service Memo SM 134, dated May 2, 2003. The Director of the Federal Register approved this incorporation by reference under 5 U.S.C. 552(a) and 1 CFR part 51. You can get copies from Goodrich Avionics Systems, Inc., 5353 52nd Street, SE, Grand Rapids, Michigan 49512-9704; telephone: (616) 949-6600; facsimile: (616) 977-6898. You may view this information at FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
(g) When does this amendment become effective? This amendment becomes effective on July 21, 2003.
