84-10-01 R1: Bladder Fuel Cells

84-10-01 R1 CESSNA: Amendment 39-4863 is further amended by Amendment 39-5940. Applies to the following series and serial numbered airplanes certificated in any category: \n\n\nSERIES\nSERIAL NUMBERS\n180\n30000 thru 50911; 18050912 thru 18053000 (1953 thru 1978) 18053001 thru 18053203 (1979 thru 1981) (optional tanks only) \n182\n33000 thru 53007; 18253008 thru 18266590 (1956 thru 1978)\nR182\nR18200001 thru R18200583 (1978) \n185\n185-0001 thru 18503683 (1961 thru 1978) \n18503684 thru 18504414 (1979 thru 1983) \n(optional tanks only) \n188\n188-0446 thru 18803856 (1972 thru 1981) \n(wing tanks only) \n18800967T thru 18803966T (1972 thru 1983) \nT188\nT18803307T thru T18803966T (1979 thru 1983)\n190/195\n7001 thru 7999; 16000 thru 16183 \n210-5 (205)\n205-0001 thru 205-0577 (1963 and 1964) \n206, U206, TU206 \n206-0001 thru U20604649 (1964 thru 1978)\nP206, TP206\nP206-0001 thru P20600647 (1965 thru 1970) \n207, T207\n20700001 thru 20700771 (1969 thru 1984)\n210\n57001 thru 57575; 21057576 thru 21058818 (1960 thru 1966)\nT210\nT210-0001 thru T210-0197 (1966) \nA182\nA182-0001 thru A182-0146 (1966 thru 1974)\nF182\nF18200001 thru F18200094 (1976 thru 1978)\nFR182\nFR18200001 thru FR18200020 (1978) \n\n\tCompliance: Required as indicated, unless already accomplished: \n\n\tTo prevent power loss or engine stoppage due to water contamination of fuel system, accomplish the following: \n\n\t(a)\tWithin the next 50 hours time-in-service after the effective date of this AD, on all applicable airplanes, install quick drains in the fuel tank sumps and fuel tank reservoirs where applicable, in accordance with the kits specified by Cessna Service Letters SE79-45 dated September 10, 1979, and SE84-8 dated March 16, 1984, or using equivalent aircraft standard hardware. \n\n\t(b)\tWithin the next 50 hours time-in-service after the effective date of this AD, inspect the fuel tank filler area for proper sealing in accordance with the following: \n\n\t\t(1)\tOn all applicable airplanes: \n\n\t\t\t(i)\tVisually inspect the wing aft of the fuel filler for indications of inflight fuel leakage. \n\n\t\t\t(ii)\tVisually inspect the fuel cap locking mechanism and seals for cracking, distortion, and any condition which might prevent sealing. \n\n\t\t\t(iii)\tRemove the fuel filler caps and inspect the adapter sealing face for distortion, scratches, corrosion or any condition which may prevent the cap from sealing. \n\n\t\t(2)\tIn addition, on all applicable airplanes except models 190 and 195 airplanes: \n\n\t\t\t(i)\tVisually check the sealing and security of the attachment of the adapter flange to the adapter plate paying particular attention to the adhesive (if present) between the parts. \n\n\t\t\t(ii)\tCheck the fuel cap seal by actuating the locking tab and noting that force is maintained between the cap, seal, and adapter when the tab is in the overcenter locked position or conduct a fuel cap seal test in accordance with Cessna Single Engine Service Information Letter SE82-34 dated July23, 1982. \n\n\t\t(3)\tCorrect any deficiencies disclosed by the above inspections by parts replacement or adjustment, as required, before returning the airplane to service. \n\n\t(c)\tWithin the next 50 hours time-in-service after the effective date of this AD, on all applicable airplanes, except models 190 and 195, conduct an inspection for fuel tank wrinkles in accordance with the following: \n\n\t\t(1)\tDrain the wing fuel tanks. \n\n\t\t(2)\tNote any wrinkles which retain fluid after draining. Remove diagonal wrinkles across the \ninboard rear corner in the vicinity of the fuel tank drain by installation of Cessna drain kit described in Service Letter SE84-9 dated March 23, 1984, or by replacement of the fuel bladder. Verify that no wrinkles exist in the tank sump drain area before returning the airplane to service. \n\n\tNOTE: The manufacturer has identified some new bladder cells which may require installation with a special adapter to prevent the formation of the above described wrinkles and has included this part with these bladder cells. Use of this part, or the drain kit, may be necessary to eliminate these wrinkles. \n\n\t\t(3)\tIf wrinkles are found in the tank bottom at a location other than diagonally across the inboard rear corner, determine the amount of fluid which is trapped by these wrinkles in accordance with the following: \n\n\t\t\t(i)\tPlace the airplane in the normal ground (water) attitude. \n\n\t\t\t(ii)\tService tank(s) with enough fuel to completely cover bottom of tank surface. Drain tank and note any wrinkles which retain fuel. \n\n\t\t\t(iii)\tDirect all trapped fluid to the tank drain area, using a non-absorbent squeegee or other tool compatible with the fuel bladder, and drain and measure the fluid retained in both tanks. \n\n\t\t\t(iv)\tIf this total does not exceed three ounces, no further action is required. \n\n\t\t\t(v)\tIf the total quantity drained exceeds three ounces, check the snaps and fasteners \nfor security. If necessary, blend and smooth the tankbottom to remove wrinkles. Blending may include replacement of the protective tape on the corners or edges to maintain a tank surface which will not trap excess fluid. Caution: Excessive blending or smoothing may cause leaks to develop in the tank. \n\n\t\t\t(vi)\tIf the tanks trap fluid in excess of three ounces after compliance with paragraph (v) above accomplish either paragraph (A) or paragraph (B) as follows: \n\n\t\t\t\t(A)\tFabricate using letters at least .10 inches in height, and install a placard in full view of the pilot which states as follows: \n\n\t\t\t\t\t"Prior to flight following exposure to rain, sleet, snow, or after fueling from an unfiltered fuel source: \n\n\t\t\t\t\t1.\tDrain and catch the contents of the fuel gascolator, wing, and (if equipped) reservoir tank sumps and check for water contamination. \n\n\t\t\t\t\t2.\tPlace the airplane on a level surface and lower the tail to within 5 inches of the ground (on nose gear airplanes). \n\n\t\t\t\t\t3.\tRock the wings 10 inches up and 10 inchesdown at least 12 times. \n\n\t\t\t\t\t4.\tDrain and catch the contents of the fuel gascolator, wing, and (if equipped) reservoir tank sumps and check for water contamination. \n\n\t\t\t\t\t5.\tIf water is found in step 4 above, repeat steps 3 and 4 until no additional water is detected, or drain the entire airplane fuel system. \n\n\t\t\t\t(B)\tInstall reduced diameter (raised filler neck) fuel caps on all fuel filler openings in accordance with Cessna Service Kit SK182-85 dated September 10, 1984. If SK182-85 is accomplished, paragraph (d) below no longer applies. \n\n\t(d)\tWithin 12 months after initial compliance with this AD, and each 12 months thereafter, reinspect the fuel filler installation of airplanes that require the placard per paragraph (c)(3)(vi) in accordance with paragraph (b) of this AD. \n\n\t(e)\tThe placard required by paragraph (c)(3)(vi) may be fabricated and installed by the airplane owner, or operator, providing that this person possesses at least a private pilot license. \n\n\t(f)\tAirplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished if it is determined that no water is present in the tank from which fuel will be used. \n\n\t(g)\tAn equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Office, Federal Aviation Administration, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. Fuel cells and quick drain valves that are approved for the applicable airplanes are approved as an equivalent means of compliance in replacement of corresponding parts required to be installed \nby this AD. \n\n\tAll persons affected by this directive may obtain copies of the document(s) referred to herein upon request to Cessna Aircraft Company, Customer Service, P.O. Box 1521, Wichita, Kansas 67201; or may examine the document(s) referred to herein at the Federal Aviation Administration, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. \n\n\tThis amendment revises AD 84-10-01, Amendment 39-4863 (49 FR 21507, May 22, 1984), effective May 22, 1984. \n\n\tThis amendment, 39-5940, becomes effective on July 5, 1988.