AD 2002-14-27 Airworthiness Directives; Fokker Model F.28 Mark 0070, 0100, 1000, 2000, 3000, and 4000 Series Airplanes

Models named: F.28 Mark 0070, 0100, 1000, 2000, 3000, 4000 series. Read the applicability below — it usually turns on serial or part numbers too.

All Model F.28 Mark 0070, 0100, 1000, 2000, 3000, and 4000 series airplanes; certificated in any category. Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (e) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Required as indicated, unless accomplished previously. To prevent takeoff with snow, ice, or frost on the critical surfaces of the airplane, which could result in reduced controllability of the airplane; accomplish the following: Restatement of Requirements of AD 94-25-03, Amendment 39-9087 (a) Within 10 days after December 21, 1994 (the effective date of AD 94-25-03, amendment 39-9087), incorporate the following into the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) (this may be accomplished by inserting a copy of this AD in the AFM): “Wing De-Icing/Anti-Icing Prior To Takeoff Caution The Model F.28 series airplane has a wing design with no leading edge high lift devices, such as slats. Wings without leading edge high lift devices are particularly susceptible to loss of lift due to wing icing. Minute amounts of ice or other contamination (equivalent to medium grit sandpaper) on the leading edges or upper wing surfaces can cause significant reduction in the stall angle-of-attack. This can increase stall speed up to 30 knots. The increased stall speed can be well above the stall warning (stick shaker) activation speed. Takeoff shall not be attempted unless the pilot-in-command has ensured that the aircraft surfaces are free of ice, frost, and snow accumulation, as required by §§ 91.527 and 121.629 of the Federal Aviation Regulations (FAR). In addition, takeoff shall not be attempted when the Outside Air Temperature (OAT) is below 6 degrees C (Centigrade) [42 degrees F (Fahrenheit)]; and either the difference between the dew point temperature and OAT is less than 3 degrees C (5 degrees F), or visible moisture (rain, drizzle, sleet, snow, fog, etc.) is present, unless the operator complies with either Option 1 or Option 2 below: Option 1 The leading edge and upper wing surfaces have been physically checked for ice/frost/snow and the flight crew verifies that a visual check and a physical (hands-on) check of the leading edge and upper wing surfaces has been accomplished and that the wing is clear of ice/frost/snow accumulation; or Option 2 The following takeoff procedure is used: Warning The following technique cannot be used unless the pilot-in-command has ensured that the aircraft surfaces are free of ice, frost, and snow, as required by §§ 91.527 and 121.629 of the FAR. • (All Marks, except Mark 0100 and Mark 0070) When using flight director for takeoff, select HDG mode and 10 degrees pitch attitude. • Select the largest flap setting that is permissible for the takeoff weight/altitude/temperature conditions. • (All Marks, except Mark 0100 and Mark 0070) Use rated takeoff thrust. • (Mark 0100 and Mark 0070) Use takeoff/go-around (TOGA) thrust. • Do not use flexible thrust. • At V R rotate slowly (less than 3 degrees per second) to 10 degrees pitch attitude. • When positively climbing, select gear UP. • Do not exceed 10 degrees pitch until airspeed is above V 2 + 20 KTS. • When above V 2 + 20 KTS, slowly increase the pitch attitude, keeping the speed above V 2 + 20 KTS. • Retract the flaps at or above V FR + 20 KTS. Notes to Option 2 1. The available field length must be greater than or equal to 120 percent of the takeoff distance required by regulation for the actual gross weight. Also, the 20 percent increase in takeoff distance must be accounted for in the obstacle clearance analysis. Weight must be off-loaded, if necessary, to meet these conditions. 2. (Mark 0100 and Mark 0070) Do not follow the Flight Director pitch command during rotation for takeoff and initial climb, as this will result in exceeding the recommended maximum pitch angle of 10 degrees before reaching the speed of V 2 + 20 KTS. 3. (Mark 0100 and Mark 0070) Do not engage the autopilot until leaving the Automated Flight Control and Augmentation System (AFCAS) takeoff (TO) mode. 4. For the case of an engine failure, refer to the applicable procedure in Section 4.17.01 Single Engine Operation of the F.28 Mark 0100 (Fokker 100) and F.28 Mark 0070 (Fokker 70) AFM, or Section 1.7.4 Operation Under Abnormal Conditions of the F.28 FHB, as applicable. 5. During takeoff, the first indication of wing contamination will probably be airframe buffet when the pitch angle is increased above 10 degrees, followed by wing drop and insufficient climb rate. Do not exceed 10 degrees pitch until airspeed is above V 2 + 20 KTS.” This action is required until the requirements of paragraph (c) of this AD are accomplished, or the actions specified in paragraphs (d) and (e) of this AD are accomplished. Note 2: If an operator elects to implement in its fleet only one of the two options specified in this paragraph, the other OPTION does not have to be included in the Limitations Section of the AFM. However, the OPTION that is implemented must be incorporated in the AFM verbatim as it appears in this paragraph. New Requirements of This AD Modification (b) Except as provided in paragraph (d) of this AD: Within 18 months after the effective date of this AD, modify the wing anti-ice system for operation on the ground as specified in paragraph (b)(1) or (b)(2) of this AD, as applicable. (1) For Model F.28 Mark 0070 and 0100 series airplanes, modify in accordance with Fokker Service Bulletin SBF100-30-018, Revision 1, Appendix I, Appendix 1, dated August 14, 1999. (2) For Model F.28 Mark 1000, 2000, 3000, and 4000 series airplanes, modify in accordance with Fokker Service Bulletin F28/30-031, Appendix I, Revision 1, dated May 4, 1998; and Fokker Proforma Service Bulletin F.28/30-032, including Appendix 1, dated December 1, 1999; as applicable. Manual Change Notification (MCNO) (c) Prior to further flight after accomplishing the modification required by paragraph (b) of this AD, remove the AFM revisions required by paragraph (a) of this AD, and incorporate the flight manual changes specified in Fokker MCNO F100-003, dated September 19, 1997 (for Fokker Model F.28 Mark 070 and 0100 series airplanes); and Fokker MCNO F28-003, dated September 5, 1997 (for Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 series airplanes); as applicable. Accomplishment of the actions specified in paragraphs (b) and (c) of this AD constitute terminating action for the requirements of this AD. Note 3: Incorporation of the leading edge thermal anti-ice modification and associated operating instructions does not relieve the requirement that airplane surfaces are free of ice, frost, and snow accumulation as required by §§ 91.527 and 121.629 of the Federal Aviation Regulations (14 CFR 91.527 and 121.629). Acceptable Method of Compliance With the Requirements of Paragraphs (b) and (c) of This AD (d) For Fokker Model F.28 Mark 0100 series airplanes on which a “Contaminant/Fluid Integrity Measuring System” (C/FIMS”) has been installed in accordance with Supplemental Type Certification ST291CH, as amended on August 20, 1998: Prior to further flight after accomplishment of STC ST291CH, as amended on August 20, 1998, remove the AFM revisions required by paragraph (a) of this AD, and incorporate the following into the Limitations Section of the FAA-approved AFM (This may be accomplished by inserting a copy of this AD in the AFM): “Wing De-Icing/Anti-Icing Prior To Takeoff Caution The Model F.28 series airplane has a wing design with no leading edge high lift devices, such as slats. Wings without leading edge high lift devices are particularly susceptible to loss of lift due to wing icing. Minute amounts of ice or other contamination (equivalent to medium grit sandpaper) on the leading edges or upper wing surfaces can cause significant reduction in the stall angle-of-attack. This can increase stall speed up to 30 knots. The increased stall speed can be well above the stall warning (stick shaker) activation speed. Takeoff shall not be attempted unless the pilot-in-command has ensured that the aircraft surfaces are free of ice, frost, and snow accumulation, as required by §§ 91.527 and 121.629 of the Federal Aviation Regulations (FAR). In addition, takeoff shall not be attempted when the Outside Air Temperature (OAT) is below 6 degrees C (Centigrade) [42 degrees F (Fahrenheit)]; and either the difference between the dew point temperature and OAT is less than 3 degrees C (5 degrees F), or visible moisture (rain, drizzle, sleet, snow, fog, etc.) is present; unless the operator complies with Option 1, Option 2, or Option 3. Option 1 (i) Operate the C/FIMS” in accordance with AFM Supplement AlliedSignal Aerospace Canada Document Number 6C-486, Revision 2, dated August 4, 1999. (ii) C/FIMS” is an advisory system that must not be used as the primary means of determining whether the airplane should be initially deiced or anti-iced or used as the primary means of determining that the fluid has failed. (iii) C/FIMS” may be used only for the time periods covered by the dicing/anti-icing holdover time tables. C/FIMS” may not be used when the holdover time tables have been exceeded; or If the C/FIMS TM is not operational: Option 2 The leading edge and upper wing surfaces have been physically checked for ice/frost/snow and the flight crew verifies that a visual check and a physical (hands-on) check of the leading edge and upper wing surfaces has been accomplished and that the wing is clear of ice/frost/snow accumulation; or If the C/FIMS TM is not operational: Option 3 The following takeoff procedure is used: Warning The following technique cannot be used unless the pilot-in-command has ensured that the aircraft surfaces are free of ice, frost, and snow, as required by §§ 91.527 and 121.629 of the FAR. • Select the largest flap setting that is permissible for the takeoff weight/altitude/temperature conditions. • Use takeoff/go-around (TOGA) thrust. • Do not use flexible thrust. • At VR rotate slowly (less than 3 degrees per second) to 10 degrees pitch attitude. • When positively climbing, select gear UP. • Do not exceed 10 degrees pitch until airspeed is above V 2 + 20 KTS. • When above V 2 + 20 KTS, slowly increase the pitch attitude, keeping the speed above V 2 + 20 KTS. • Retract the flaps at or above V FR + 20 KTS. Notes to Option 3 1. The available field length must be greater than or equal to 120 percent of the takeoff distance required by regulation for the actual gross weight. Also, the 20 percent increase in takeoff distance must be accounted for in the obstacle clearance analysis. Weight must be off-loaded, if necessary, to meet these conditions. 2. Do not follow the Flight Director pitch command during rotation for takeoff and initial climb, as this will result in exceeding the recommended maximum pitch angle of 10 degrees before reaching the speed of V 2 + 20 KTS. 3. Do not engage the autopilot until leaving the Automated Flight Control and Augmentation System (AFCAS) takeoff (TO) mode. 4. For the case of an engine failure, refer to the applicable procedure in Section 4.17.01 Single Engine Operation of the F.28 Mark 0100 (Fokker 100) AFM. 5. During takeoff, the first indication of wing contamination will probably be airframe buffet when the pitch angle is increased above 10 degrees, followed by wing drop and insufficient climb rate. Do not exceed 10 degrees pitch until airspeed is above V 2 + 20 KTS.” Accomplishment of the actions specified in this paragraph after the installation of STC ST291CH, as amended on August 20, 1998, constitute terminating action for the requirements of this AD. Note 4: Operators should note that, while Option 1 specified in paragraph (d) of this AD must be incorporated into the Limitations Section of the AFM, operators may elect to incorporate either both or only one of the other two options specified in paragraph (d) of this AD. Only Option 1 and the elected option(s) need to be incorporated into the AFM. However, any option that is incorporated into the AFM must be identical to the option wording specified in paragraph (d) of this AD. Note 5: Installation of the Contaminant/Fluid Integrity Measuring System (C/FIMS  TM ) in accordance with Supplemental Type Certification ST291CH, as amended on August 20, 1998, and accomplishment of the actions specified in paragraph (d) of this AD, do not relieve the requirement that airplane surfaces are free of ice, frost, and snow accumulation as required by §§ 91.527 and 121.629 of the Federal Aviation Regulations (14 CFR 91.527 and 121.629). Alternative Methods of Compliance (e) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, International Branch, ANM-116. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, International Branch, ANM-116. Note 6: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116. Special Flight Permits (f) Special flight permits may be issued in accordance with §§ 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. Incorporation by Reference (g) The actions required by paragraphs (b) and (c) of this AD shall be done in accordance with Fokker Service Bulletin SBF100-30-018, Appendix I, Revision 1, dated August 14, 1999; Fokker Service Bulletin F28/30-031, Appendix I, Revision 1, dated May 4, 1998; Fokker Proforma Service Bulletin F28/30-032, including Appendix 1, dated December 1, 1999; Fokker Manual Change Notification MCNO F100-003, dated September 19, 1997; and Fokker Manual Change Notification MCNO F28-003, dated September 5, 1997. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Fokker Services B.V., P.O. Box 231, 2150 AE Nieuw-Vennep, The Netherlands. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. Effective Date (h) This amendment becomes effective on August 29, 2002. Issued in Renton, Washington, on July 12, 2002. Lirio Liu-Nelson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 02-18624 Filed 7-24-02; 8:45 am] BILLING CODE 4910-13-U