AD 87-24-07 R1

87-24-07 R1 GULFSTREAM AEROSPACE CORPORATION: Amendment 39-5774 as amended by amendment 39-5840. Applies to Models 690, 690A, 690B, 690C, 690D, 695, 695A, and 695B (all serial numbers) airplanes certificated in any category.

Compliance: Required within the next 50 hours' time-in-service after the effective date of this AD, unless already accomplished.

(a) To prevent engine flameout when in or departing an icing environment, accomplish the following: (1) Revise the airplane POH/AFM by inserting or assuring that the appropriate Gulfstream published revision has been inserted as defined by the following listing:

Model 690, Revision No. 23, dated May 20, 1987 Model 690A, Revision No. 30, dated May 20, 1987 Model 690B, Revision No. 23, dated May 20, 1987 Model 690C, Revision No. 21, dated April 9, 1987 Model 690D, Revision No. 12, dated April 9, 1987 Model 695, Revision no. 12, dated April 9, 1987 Model 695A, Revision No. 20, dated April 9, 1987 Model 695B,Revision No. 9, dated April 9, 1987

If the listed revision is not available, revise the POH/AFM by inserting Appendix 1 of this AD in the "LIMITATIONS" section of the POH/AFM. Appendix 1 procedures supersede any other POH/AFM procedures which may be contradictory. NOTE 1: If the above actions have been accomplished in compliance with AD 86-24-12, no further action is required in order to comply with paragraph (a)(1) of this AD. (2) For those airplanes with ignition systems having a continuous duty cycle of less than 1 hour: (i) Fabricate and install a placard on the instrument panel in clear view of the pilot stating, "This airplane is prohibited from flight into known icing," and operate the airplane in accordance with this limitation. This placard must consist of a minimum of 0.1 inch high letters with white and red contrasting letter and background colors and may be of a plastic adhesive type. (ii) The requirements of section (a)(2)(i) are no longer applicable when the aircraft ignition system having a continuous duty cycle of less than 1 hour is modified to increase the duty cycle to 1 hour or more in accordance with Gulfstream Service Information Nos. SI-211 and/or SI-212 both dated June 30, 1986.

(b) The requirements of paragraph (a) of this AD are no longer applicable when the airplane is modified in accordance with Gulfstream Custom Kit Nos. 138 dated April 15, 1987, or 139 dated May 28, 1987, or by the addition of other FAA approved automatic relight ignition systems for both engines. NOTE 2: Automatic-relight ignition is a system which automatically energizes engine ignition without pilot action when engine RPM or torque decays below a specified level and de-energizes engine ignition when RPM or torque exceeds the specified level. It is not synonymous with CONTINUOS IGNITION.

(c) The requirements of paragraph (a)(1) and (a)(2)(i) of this AD may be accomplished by the holder of a pilot certificate issued under Part 61 of the FAR on any airplane owned or operated by the pilot, and which is not used under Part 121 or 135. The person accomplishing these actions must make the appropriate airplane maintenance record entry as prescribed by FAR 91.173.

(d) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished.

(e) An equivalent means of compliance with this AD may be used if approved by the Manager, Airplane Certification Branch, ASW-150, FAA, Fort Worth, Texas 76193-0150; telephone (817) 624-5150.

All persons affected by this directive may obtain copies of the documents(s) referred to herein upon request to the Gulfstream Aerospace Corporation, Wiley Post Airport, P.O. Box 22500, Oklahoma City, Oklahoma 73123; Telephone (405) 789-5000; or may be examined at the FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106.

This AD revises AD 87-24-07, Amendment 39-5774, which superseded AD 86-24-12, Amendment 39- 5483(52 FR 43849; November 17, 1987.). This amendment, 39-5840, becomes effective on February 9, 1988.

APPENDIX I Supplement to the POH/AFM Gulfstream Aerospace Corporation Models 690, 690A, 690B, 690C, 690D, 695, 695A, and 695B Airplanes

Continuous ignition switch shall be assured by selecting Manual IGN or IGN Override or IGN OVRD on the ignition switch as appropriate during all operations in actual or potential icing conditions described herein: (1) During takeoff and climb out in actual or potential icing conditions. (2) When ice is visible on, or shedding from propeller(s), spinner(s), or leading edge(s). *(3) Before selecting ENG INLET, when ice has accumulated. (4) Immediately, any time engine flameout occurs as a possible result of ice ingestion. (5) During approach and landing while in or shortly following flight in actual or potential icing conditions. *Note: If icing conditions are entered in flight without the engine anti-icing system having beenselected, switch one ENGINE system to ENG INLET ON position. If the engine runs satisfactorily, switch the second ENGINE system to the ENG INLET ON position and check that the second engine continues to run satisfactorily.

CAUTION Flight in actual or potential icing conditions will be limited by duty cycle of the ignition system. Ignition system time limits must be observed to prevent exceeding duty cycle times. Operator should verify these limits for his particular installation. For the purpose of this supplement, the following definition applies: "Potential icing conditions in precipitation or visible moisture meteorological conditions: (1) Begin when the OAT is +5 degrees C (+41 degrees F) or colder, and (2) End when the OAT is +10 degrees C (+50 degrees F) or warmer." The procedures and conditions described in this appendix supersede any other POH/AFM procedures and conditions which may be contradictory.