Airworthiness Directives; CESSNA Models 150F, G, H, J, K, L, F150F, G, H, J, K, L, A150K, L, FA150K, L, 172F, G, H, I, K, L, F172F, G, H, K, R172E, F, G, H, FR172E, F, G, H, 177, 177A, B, 177RG, F177RG, 182E, F, G, H, J, K, L, M, N, A182J, K, L, M, N, 205, 205A, 206, P206, P206A, B, C, D, E, and , TP206A, B, C, D, E, U206, U206A, B, C, D, E, and , TU206A, B, C, D, E, 207 and T207, 210D, E, F, G, H, J, K, T210F, G, H, J

TP206, TU206, 207, T207, 210, T210, P210, 205, 336, 337, T337, P337, T303, F150, FA150, FRA150, FA152, F152, FP172, F172, FR172, F177RG, F182, FR182, F337, FP337 Series Airplanes PDF Copy (If Available): Preamble Information AGENCY: Federal Aviation Administration, DOT DATES: Effective September 24, 1990. Regulatory Information 87-20-03 R2 CESSNA: Amendment 39-5729, as revised by Amendment 39-5863, is further revised by Amendment 39-6669. Docket No. 86-CE-71-AD. Applicability: To the following model airplanes, certificated in any category. Models Serial Numbers 150A, 150B, 150C, 150D, 150E, 150F, 150G, 150H, 150J, 150K, 150L, 150M 15059019 thru 15079405 A150K, A150L, A150M A1500001 thru A1500734 152, A152 All 170, 170A, 170B 18000 through 27169 172, 172A, 172B, 172C, 172D, 172E, 172F, 172G, 172H, 172I, 172K, 172L, 172M, 172N, 172P, 172Q All P172D P17257120 thru P17257188 R172E, R172F, R172G, R172H, R172J All R172K R1722000 thru R1723454 172RG 172RG0001 thru 172RG1191 175, 175A 55001 thru 56777 175B, 175C 17556778 thru 17557119 177, 177A, 177B, 177RG All 180, 180A 30000 thru 32999 180A, 180B, 180C 50000 thru 50911 180D, 180E, 180F, 180G, 180H, 180J, 180K 18050912 thru 18053203 182, 182A, 182B, 182C, 182D, 182E, 182F, 182G, 182H, 182J, 182K, 182L, 182M, 182N, 182P, 182Q, 182R, T182, R182,TR182 All 185, 185A, 185B, 185C, 185D, 185E, A185E, A185F All 188, 188A, A188, A188A, 188B, A188B, T188C All 190, 195, 195A, 195B 7001 thru 7999, and 16000 thru 16183 206, U206, U206A, U206B, U206C, U206D, U206E, U206F, U206G, TU206A, TU206B, TU206C, TU206D, TU206E, TU206F, TU206G All P206, P206A, P206B, P206C, P206D, TP206A, TP206B, TP206C, TP206D P206-0001 thru P206-0603, & P206E, TP206E P20600604 thru P20600647 207, T207, 207A, T207A All 210, 210A, 210B, 210C, 210D, 210E, 210F, 210G, 210H, 210J, 210K, 210L, 210M, 210N, P210N, T210F, T210G, T210H, T210J, T210K, T210L, T210M, T210N, 210R, T210R, P210R All 210-5 (205), 210-5A (205A) 205-0001 thru 205-0577 336 336-0001 thru 336-0195 337, 337A, 337B, 337C, 337D, 337E, 337F, 337G, 337H, T337B, T337C, T337D, T337E, T337F, T337G, T337H, P337H, T337H-SP All T303 All F150G, F150H, F150J, F150K, F150L, F150M, FA150K, FA150L, FRA150L, FRA150M All FA152, F152 All FP172 FP172-0001 thru FP172-0003 F172F, F172G, F172H, F172K, F172L, F172M, F172N, F172P, FR172E, FR172F, FR172G, FR172H, FR172J, FR172K All F177RG All F182P, F182Q All FR182 All F337E, F337F, F337G, F337H All FP337 All Compliance: Required as follows, unless already accomplished per AD 87-20-03 R1, Amendment 39-5863. I. For airplanes operating for hire: (A) For airplanes having less than 1,000 hours time-in-service (TIS) on the effective date of this AD, accomplish the AD requirements prior to the accumulation of 1,100 hours TIS; (B) For airplanes having 1,000 or more hours TIS on the effective date of this AD, accomplish the AD requirements within the next 100 hours TIS; (C) Following the actions of (A) or (B) above, repeat the inspection requirements of this AD at each 100 hours TIS. These inspections can be accomplished at the next scheduled inspection or the next 100 hours, whichever is later. II. For airplanes operating under FAR Part 91 (not for hire): (A) For airplanes having less than 1,000 hours TIS on the effective date of this AD, accomplish the AD requirements at the next annual inspection after the accumulation of 1,000 hours TIS; (B) For airplanes having 1,000 or more hours TIS on the effective date of this AD, accomplish the AD requirements at the next annual inspection; (C) Following the actions of (A) or (B) above, repeat the AD requirements at each annual inspection thereafter. To assure proper engagement of the seat locking mechanism and to preclude inadvertent seat slippage, accomplish the following on each pilot and copilot seat and all associated seat rails: NOTE 1: Paragraph (a) of this AD is essentially unchanged from AD 87-20-03 R1, Amendment 39-5863 and is reprinted here for the convenience of the reader. (a) In accordance with the appropriate compliance time requirement above, accomplish the following: (1) Measure each hole in the seat track(s) for excessive wear. When checking these holes for wear, an allowance of 0.020 inches below the edge of the normal surface is permitted for the required measurement. (i) If the wear dimension across any hole exceeds 0.36 inches but does not exceed 0.42 inches (see Figure 1), continue to measure each hole every 100 hours TIS for excessive wear. (ii) If the wear dimension across any hole exceeds 0.42 inches, prior to further flight, replace the seat track. (2) Visually inspect the seat rail holes for dirt and any debris, which may preclude engagement of the seat pin(s). Prior to further flight, remove any such material. (3) Lift up on the forward edge of each seat to eliminate all vertical play. In this position, measure the depth of engagement of each seat pin. If the engagement of any pin is less than 0.15 inches (see Figure 2), prior to further flight, replace or repair necessary components to achieve a seat pin engagement of 0.15 inches or greater. If the track is worn, this dimension is measured from the worn surface, not the manufactured surface. (4) Visually inspect seat rollers for flat spots. Assure all rollers and washers, which are meant to rotate, turn freely on their axle bolts (or bushings if installed). Prior to further flight, replace rollers having flat spots and any worn washers. If there is any binding between the bores of the rollers, washers, and axle bolts (or bushings if installed), prior to further flight, remove, clean, and reinstall these parts. NOTE 2: Do not lubricate rollers, washers, axle bolts or bushings as the lubricant will attract dust and other particles which can cause binding. (5) Measure the wall thicknesses of the roller housing and the tang (see Figure 2). If the tang thickness has worn to less than 1/2 the housing thickness, prior to further flight, replace the roller housing. (6) Check the spring(s) that keep the lock pin(s) in position in the track holes for positive engagement action. Prior to further flight, replace any spring which does not provide positive engagement. (7) Visually inspect the seat tracks for cracks in accordance with Cessna Single Engine Service Information Letter SE83-6, dated March 11, 1983. Prior to further flight, replace any seat rail exceeding the crack criteria as specified in SE83-6 with an airworthy rail. (b) The options listed in AD 87-20-03 R1, Amendment 39-5863, for the temporary operation of the airplane are no longer an acceptable means of compliance with the requirements of this AD, but may be retained if desired. (c) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (d) Any parts replaced per this AD are exempt from the inspections required herein until such parts have attained 1,000 hours TIS. (e) An alternate method of compliance or adjustment of the initial or repetitive compliance times, which provides an equivalent level of safety, may be approved by the Manager, Wichita Aircraft Certification Office, Federal Aviation Administration, 1801 Airport Road, Room 100, Wichita, Kansas 67209. NOTE 3: The request should be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office. All persons affected by this directive may obtain copies of the document referred to herein upon request to the Cessna Aircraft Company, Customer Service, P.O. Box 1521, Wichita, Kansas 67201; or may examine this document at the Federal Aviation Administration, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. Airworthiness Directive 87-20-03 R2 revises AD 87-20-03 R1 (Amendment 39-5863) which revised AD 87-20-03 (Amendment 39-5729). This amendment (39-6669, AD 87-20-03 R2) becomes effective on September 24, 1990. Footer Information Comments FAA.gov Home | Privacy Policy | Web Policies & Notices | Contact Us | Help Readers & Viewers: PDF Reader | MS Word Viewer | MS PowerPoint Viewer | MS Excel Viewer | WinZip 1 [Federal Register: September 15, 2008 (Volume 73, Number 179)] [Rules and Regulations] [Page 53105-53113] From the Federal Register Online via GPO Access [wais.access.gpo.gov] [DOCID:fr15se08-1] –––––––––––––––––––––––––––––––––– DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2008-0052; Directorate Identifier 2008-NE-01-AD; Amendment 39-15672; AD 2008-19-05] RIN 2120-AA64 Airworthiness Directives; Engine Components, Inc. (ECi) Reciprocating Engine Cylinder Assemblies AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. –––––––––––––––––––––––––––––––––– SUMMARY: The FAA is adopting a new airworthiness directive (AD) for Lycoming Engines (formerly Textron Lycoming) models 320, 360, and 540 series, ''Parallel Valve'' reciprocating engines, with certain Engine Components, Inc. (ECi) cylinder assemblies, part number (P/N) AEL65102 series ''Titan'', installed. This AD requires initial and repetitive visual inspections and compression tests to detect cracks at the head-to-barrel interface, replacement of cylinder assemblies found cracked, and replacement of certain cylinder assemblies, at new reduced times-in-service. This AD results from reports of 45 failures with head separations of ECi cylinder assemblies. We are issuing this AD to prevent loss of engine power due to cracks at the head-to-barrel interface in the cylinder assemblies and possible engine failure caused by separation of a cylinder head, which could result in loss of control of the aircraft. DATES: This AD becomes effective October 20, 2008. ADDRESSES: You can get the service information identified in this AD from Engine Components, Inc., 9503 Middlex, San Antonio, TX 78217; Phone (800) 324-2359; fax (210) 820-8102; http://www.eci2fly.com. The Docket Operations office is located at Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-0001. FOR FURTHER INFORMATION CONTACT: Peter W. Hakala, Aerospace Engineer, Special Certification Office, FAA, Rotorcraft Directorate, 2601 Meacham Blvd., Fort Worth, TX 76193; e- mail: peter.w.hakala@faa.gov; telephone (817) 222-5145; fax (817) 222-5785. 2 SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to Lycoming Engines (formerly Textron Lycoming) models 320, 360, and 540 series, ''Parallel Valve'' reciprocating engines, with certain Engine Components Inc. (ECi) cylinder assemblies, part number (P/N) AEL65102 series ''Titan'', installed. We published the proposed AD in the Federal Register on May 19, 2008 (73 FR 28756). That action proposed to require initial and repetitive visual inspections and compression tests to detect cracks at the head-to- barrel interface, replacement of cylinder assemblies found cracked, and replacement of certain cylinder assemblies, at new reduced times-in-service. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647-5527) is provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. Request To Reduce the Economic Impact One commenter, the Aircraft Owners and Pilots Association, states that the 50-hour inspection interval should be increased to 100 hours, to reduce the economic impact of the cylinder assembly inspections. Another commenter, a private citizen, states that the cost of the 50-hour inspections was not considered in the NPRM economic estimate. We do not agree. We selected the 50-hour inspection interval so that aluminum cylinder cracks could be detected before a head separation occurred. By removing leaking cylinder heads discovered during the periodic 50-hour inspections, the probability of having an in flight head separation is greatly reduced. Also, the 50-hour inspection interval coincides with the scheduled maintenance for normal engine oil and filter changes. Also, the costs of compliance in the NPRM did include costs for the additional cylinder assembly inspections. We did not change the AD. Retiring Cylinder Assemblies at Time-Between-Overhaul Is Too Expensive One commenter, a private citizen, states that it is too expensive to retire all the subject cylinder assemblies at the normal overhaul time. Another commenter, a private citizen, states that it is unreasonable for general aviation airplane owners, in Part 91 use, to be required to retire cylinder assemblies at the time-between-overhaul or at normal engine overhaul time. We do not agree. The subject cylinder assemblies can be safely run to the normal TBO with the required 50-hour inspections, with compression tests. Because of metallurgical analysis results of the fatigue cracks in the aluminum alloy cylinder heads, and also the history of the head separation hours-in-service, the probability of a head separation is greater with the subject cylinder assemblies running past the time-between-overhaul time. Therefore, we do not consider the cylinder assemblies to be airworthy past the normal engine overhaul time. We did not change the AD. 3 Cylinder Assembly Serial Number Range Is Different in the ECi Mandatory Service Bulletin One commenter, ECi., states that the cylinder assembly serial number range in the proposed AD for the Group ''B'' cylinders is slightly different from the serial numbers listed in the ECi Mandatory service Bulletin No. 08-1. The commenter states that several additional cylinder serial numbers should be included in Group ''B''. We do not agree. We researched the cylinder assembly serial numbers in the proposed AD and they are correct. The Group ''A'' cylinder assemblies go up to serial number 35171-22. The Group ''B'' cylinder assemblies start at serial number 35239-01. We discussed the serial number comment with ECi. They agree that the serial number range in the proposed AD is correct. ECi states that they have revised the serial numbers in ECi. Mandatory Service Bulletin (MSB) No. 08-1 to match the serial numbers in the AD, and issued MSB No. 08-1, Revision 3, dated August 19, 2008. We now reference this MSB Revision 3 in the AD. Conclusion We have carefully reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD as proposed. We have determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance We estimate that this AD will affect 13,000 ECi cylinder assemblies installed in aircraft of U.S. registry. The visual inspection and compression tests will take about 4 work-hours for each engine. An individual cylinder replacement will require $1,100 for parts and 6 work-hours. Lycoming engines with a set of 4 ECi cylinders will require 12 work-hours for the cylinder replacement. Lycoming engines with a set of 6 ECi cylinders will require 16 work-hours for the cylinder replacement. We estimate 18 percent of the affected population of cylinders will be replaced. We estimate the total cost of the AD to U.S. operators to be $7,952,000. Our estimate is exclusive of any possible warranty coverage. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in subtitle VII, part A, subpart III, section 44701, ''General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ''significant regulatory action'' under Executive Order 12866; 4 (2) Is not a ''significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary at the address listed under ADDRESSES. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends 14 CFR part 39 as follows: PART 39–AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: 5 FAA Aircraft Certification Service AIRWORTHINESS DIRECTIVE www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html 2008-19-05 Engine Components, Inc. (ECi): Amendment 39-15672. Docket No. FAA-2008-0052; Directorate Identifier 2008-NE-01-AD. Effective Date (a) This airworthiness directive (AD) becomes effective October 20, 2008. Affected ADs (b) None. Applicability (c) This AD applies to the Lycoming Engines (formerly Textron Lycoming) models 320, 360, and 540 series, ''Parallel Valve'', reciprocating engines listed in Table 1 of this AD, with ECi cylinder assembly, part number (P/N) AEL65102 series ''Titan'', and with cylinder head, P/N AEL85099, installed. (1) The applicable cylinder assembly serial numbers (SNs) are SN 1138-02 through SN 35171- 22, (referred to in this AD as Group ''A'' cylinder assemblies); and (2) SN 35239-01 through SN 37016-28 (referred to in this AD as Group ''B'' cylinder assemblies). (3) Note that the cylinder assembly P/N is at the crankcase end of the cylinder assembly, and might be difficult to see. As a guide in determining if your cylinder assemblies are affected, all affected cylinder assemblies have cylinder head P/N AEL85099. The cylinder head P/N is at the top of the cylinder head, near the intake and exhaust valve springs, and is easier to locate than the cylinder assembly P/N. (4) Note that the set of numbers appearing on the cylinder, above and to the left of the SN, in the form of ''123456'' is not used for determining applicability. Table 1–Engine Models Cylinder Assembly Part Number: Installed on Engine Models: AEL65102-NST04 O-320-A1B, A2B, A2C, A2D, A3A, A3B, B2B, B2C, B2D, B2E, B3B, B3C, C2B, C2C, C3B, C3C, D1A, D1AD, D1B, D1C, D1D, D1F, D2A, D2B, D2C, D2F, D2G, D2H, D2J, D3G, E1A, E1B, E1C, E1F, E1J, E2A, E2B, E2C, E2D, E2E, E2F, E2G, E2H, E3D, E3H IO-320-A1A, A2A, B1A, B1B, B1C, B1D, B1E, B2A, D1A, D1AD, D1B, D1C, E1A, E1B, E2A, E2B AEIO-320-D1B, D2B, E1A, E1B, E2A, E2B AIO-320-A1A, A1B, A2A, A2B, B1B, C1B LIO-320-B1A 6 AEL65102-NST05 IO-320-C1A, C1B, C1F, F1A LIO-320-C1A AEL65102-NST06 O-320-A1A, A2A, A2B, A2C, A3A, A3B, A3C, E1A, E1B, E2A, E2C, (also, an O-320 model with no suffix) IO-320-A1A, A2A AEL65102-NST07 IO-320- B1A, B1B LIO-320- B1A AEL65102-NST08 O-320-B1A, B1B, B2A, B2B, B3A, B3B, B3C, C1A, C1B, C2A, C2B, C3A, C3B, C3C, D1A, D1B, D2A, D2B, D2C AEL65102-NST10 O-360-A1A, A1C, A1D, A2A, A2E, A3A, A3D, A4A, B1A, B1B, B2A, B2B, C1A, C1C, C1G, C2A, C2B, C2C, C2D, D1A, D2A, D2B IO-360-B1A, B1B, B1C HO-360-A1A, B1A, B1B HIO-360-B1A, B1B AEIO-360-B1B O-540-A1A, A1A5, A1B5, A1C5, A1D, A1D5, A2B, A3D5, A4A5, A4B5, A4C5, A4D5, B1A5, B1B5, B1D5, B2A5, B2B5, B2C5, B2C5D, B4A5, B4B5, B4B5D, D1A5, E1A, E4A5, E4B5, E4C5, F1A5, F1B5, G1A5, G2A5 IO-540-C1B5, C1C5, C2C, C4B5, C4B5D, C4C5, D4A5, D4B5, N1A5, N1A5D AEL65102-NST12 O-360- A1A, A1AD, A1D, A1F, A1F6, A1F6D, A1G, A1G6, A1G6D, A1H, A1H6, A1J, A1LD, A1P, A2A, A2D, A2F, A2G, A2H, A3A, A3AD, A3D, A4A, A4AD, A4D, A4G, A4J, A4JD, A4K, A4M, A4N, A4P, A5AD, B1A, B2C, C1A, C1C, C1E, C1F, C1G, C2A, C2B, C2C, C2D, C2E, C4F, C4P, D2A, F1A6, G1A6 HO-360 –C1A LO-360-A1G6D, A1H6 HIO-360-B1A, B1B, G1A LTO-360-A1A6D TO-360-A1A6D IO-360-B1B, B1BD, B1D, B1E, B1F, B1F6, B1G6, B2E, B2F, B2F6, B4A, E1A, L2A, M1A, M1B AEIO-360-B1B, B1D, B1E, B1F, B1F6, B1G6, B1H, B2F, B2F6, B4A, H1A, H1B O-540-A4D5, B2B5, B2C5, B2C5D, B4B5, B4B5D, E4A5, E4B5, E4B5D, E4C5, G1A5, G1A5D, G2A5, H1A5, H1A5D, H1B5, H1B5D, H2A5, H2A5D, H2B5D IO-540-C4B5, C4B5D, C4D5, C4D5D, D4A5, D4B5, D4C5, N1A5, N1A5D, T4A5D, T4B5, T4B5D, T4C5D, V4A5, V4A5D AEIO-540-D4A5, D4B5, D4C5, D4D5 7 AEL65102-NST26 IO-540-J4A5, R1A5 TIO-540-C1A, E1A, G1A, H1A AEL65102-NST38 IO-360-F1A TIO-540-AA1AD, AB1AD, AB1BD, AF1A, AG1A, AK1A, C1A, C1AD, K1AD LTIO-540-K1AD AEL65102-NST43 O-360-J2A O-540-F1B5, J1A5D, J1B5D, J1C5D, J1D5D, J2A5D, J2B5D, J2C5D, J2D5D, J3A5, J3A5D, J3C5D IO-540-AB1A5, W1A5, W1A5D, W3A5D AEL65102-NST44 O-540-L3C5D For information, the Lycoming Engines (formerly Textron Lycoming) models 320, 360, and 540 series, ''Parallel Valve'', reciprocating engines are installed on, but not limited to, the aircraft listed in the following Table 2: Table 2–Engines Installed On, But Not Limited To Engine Models: Installed on , But Not Limited To: Piper Aircraft: Tri-Pacer (PA-22 “150”, PA-22S “150”), Apache (PA-23), Pawnee (PA-25) Doyn Aircraft: Doyn-Cessna (170, 170A, 170B) Mooney Aircraft: Mark (20A) Dinfia: Ranquel (1A-46) Simmering-Graz Pauker: Flamingo (SGP-M-222) Aviamilano: Scricciolo (P-19) O-320-A1A Vos Helicopter Co.: Spring Bok Piper Aircraft: Tri-Pacer (PA-22 “150”, PA-22S “150”), Apache (PA-23) Doyn Aircraft: Doyn-Cessna (170, 170A, 170B) O-320-A1B S.O.C.A.T.A.: Horizon (Gardan) Piper Aircraft: Tri-Pacer (PA-22 “150”, PA-22S “150”), Agriculture (PA-18A “150”) Super Cub (PA -18 “150”), Caribbean (PA-22 “150”), Pawnee (PA-25) Intermountain Mfg. Co.: Call Air Texas (A-5, A-5T) Lake Aircraft: Colonial (C-1) Rawdon Bros.: Rawdon (T-1, T-15, T-15D) Shinn Engineering: Shinn (2150-A) Dinfia: Ranquel (1A)46) Neiva: (1PD-5802) O-320-A2A Sud: Gardan-Horizon (GY-80) 8 LaVerda: Falco (F8L Series II, America) Malmo: Vipan (MF1-10) Kingsford Smith: Autocrat (SCRM-153) Aero Commander: 100 Piper Aircraft: Tri-Pacer (PA-22 “150”, PA-22S “150”), Cherokee (PA-28 “150”), Super Cub (PA -18 “150”) Champion Aircraft: Challenger (7GCA, 7GCB, 7KC), Citabria (7GCAA, 7GCRC), Agriculture (7GCBA) Beagle: Pup (150) Artic: Interstate S1B2 Robinson: R-22 O-320-A2B Varga: Kachina 2150A Robinson: R-22 Cicare: Cicare AG O-320-A2C Bellanca Aircraft: Citabria 150 (7GCAA), Citabria 150S (7GCBC) O-320-A2D Piper Aircraft: Apache (PA-23) Doyn Aircraft: Doyn-Cessna (170, 170A, 170B) O-320-A3A Corben-Fettes: Globe Special (Globe GC-1B) Piper Aircraft: Apache (PA-23) Doyn Aircraft: Doyn-Cessna (170, 170A, 170B) O-320-A3B Teal II: TSC (1A2) Piper Aircraft: Apache (PA-23 “160”) Doyn Aircraft: Doyn-Cessna (170, 170A, 170B) O-320-B1A Malmo: Vipan (MF1-10) Piper Aircraft: Apache (PA-23 “160”) O-320-B1B Doyn Aircraft: Doyn-Cessna (170, 170A, 170B) O-320-B2A Piper Aircraft: Tri-Pacer (PA-22 “160”, PA-22S “160”) Piper Aircraft: Tri-Pacer (PA-22 “160”, PA-22S “160”) Beagle: Airedale (D5-160) Fuji-Heavy Industries: Fuji (F-200) O-320-B2B Uirapuru: Aerotec 122 O-320-B2C Robinson: R-22 O-320-B2D Maule: MX-7-160 O-320-B2E Lycon Piper Aircraft: Apache (PA-23 “160”) O-320-B3A Doyn Aircraft: Doyn-Cessna (170, 170A, 170B) 9 Piper Aircraft: Apache (PA-23 “160”) Doyn Aircraft: Doyn-Cessna (170, 170A, 170B) O-320-B3B Sud: Gardan (GY80-160) Piper Aircraft: Apache (PA-23 “160”) O-320-C1A Riley Aircraft: Rayjay (Apache) O-320-C1B Piper Aircraft: Apache (PA-23 “160”) O-320-C3A Piper Aircraft: Apache (PA-23 “160”) O-320-C3B Piper Aircraft: Apache (PA-23 “160”) Sud: Gardan (GY-80) Gyroflug: Speed Cancard O-320-D1A Grob: G115 O-320-D1F Slingsby: T67 Firefly Piper Aircraft: Cherokee (PA-28S “160”) Robin: Major (DR400-140B), Chevalier (DR-360), (R-3140) S.O.C.A.T.A.: Tampico TB9 Slingsby: T67C Firefly Daetwyler: MD-3-160 Nash Aircraft Ltd.: Petrel Aviolight: P66D Delta O-320-D2A General Avia: Pinguino Beech Aircraft: Musketeer (M-23) O-320-D2B Piper Aircraft: Cherokee (PA-28 “160”) O-320-D2J Cessna Aircraft: Skyhawk 172 O-320-D3G Piper Aircraft: Warrior II, Cadet (PA-28-161) O-320-E1A Grob: G115 O-320-E1C M.B.B. (Messerschmitt-Boelkow-Blohm): Monsun (BO-209-B) O-320-E1F M.B.B.: Monsun (BO-209-B) Piper Aircraft: Cherokee (PA-28 “140”, PA-28 “150”) Robin: Major (DR-340), Sitar, Bagheera (GY-100-135) S.O.C.A.T.A.: Super Rallye (MS-886), Rallye Commodore (MS-892) Siai-Marchetti: (S-202) F.F.A.: Bravo (AS-202/15) Partenavia: Oscar (P66B), Bucker (131 APM) Aeromot: Paulistina P-56 O-320-E2A Pezetel: Koliber 150 10 Beech Aircraft: Musketeer III (M -23III) O-320-E2C M.B.B.: Monsun (BO-209-B) O-320-E2D Cessna Aircraft: Cardinal (172-I, 177) O-320-E2F M.B.B.: Monsun (BO-209-B), Wassmer Pacific (WA-51) O-320-E2G American Aviation Corp.: Traveler Piper Aircraft: Cherokee (140) O-320-E3D Beech Aircraft: Sport IO-320-B2A Piper Aircraft: Twin Comanche (PA-30) IO-320-B1C Hi. Shear: Wing IO-320-B1D Ted Smith Aircraft: Aerostar IO-320-C1A Piper Aircraft: Twin Comanche (PA-30 Turbo) IO-320-D1A M.B.B.: Monsun (BO-209-C) IO-320-D1B M.B.B.: Monsun (BO-209-C) IO-320-E1A M.B.B.: Monsun (BO-209-C) IO-320-E1B Bellanca Aircraft IO-320-E2A Champion Aircraft: Citabria IO-320-E2B Bellanca Aircraft IO-320-F1A CAAR Engineering: Carr Midget LIO-320-B1A Piper Aircraft: Twin Comanche (PA-39) LIO-320-C1A Piper Aircraft: Twin Comanche (PA-39) AIO-320-B1B M.B.B.: Monsun (BO-209-C) AEIO-320-D1B Slingsby: T67M Firefly AEIO-320-D2B Hundustan Aeronautics Ltd.: HT-2 Bellanca Aircraft AEIO-320-E1A Champion Aircraft Bellanca Aircraft AEIO-320-E1B Champion Aircraft: Decathalon (8KCAB-CS) Bellanca Aircraft AEIO-320-E2B Champion Aircraft: Decathalon (8KCAB) O-320-A1A Riley Aircraft: Riley Twin Beech Aircraft: Travel Air (95, B-95) Piper Aircraft: Comanche (PA-24) Intermountain Mfg. Co.: Call Air (A-6) Lake Aircraft: Colonial (C-2, LA -4, 4A or 4P) O-360-A1A Doyn Aircraft: Doyn-Cessna (170B, 172, 172A, 172B) 11 Mooney Aircraft: Mark “20B” (M-20B) Earl Horton: Pawnee (Piper PA-25) Dinfia: Ranquel (1A-51) Neiva: (1PD-5901) Regente: (N-591) Wassmer: Super 4 (WA-50A), Sancy (WA-40), Baladou (WA-40), Pariou (WA-40) Sud: Gardan (GY-180) Bolkow: (207) Partenavia: Oscar (P-66) Siai-Marchetti: (S-205) Procaer: Picchio (F-15-A) S.A.A.B.: Safir (91-D) Malmo: Vipan (MF-10B) Aero Boero: AB-180 Beagle: Airedale (A-109) DeHavilland: Drover (DHA-3MK3) Kingsford-Smith: Bushmaster (J5-6) Aero Engine Service Ltd.: Victa (R-2) O-360-A1AD S.O.C.A.T.A.: Tabago TB-10 Piper Aircraft: Comanche (PA-24) Lake Aircraft: Colonial (LA -4, 4A or 4P) Doyn Aircraft: Doyn-Beech (Beech 95) Mooney Aircraft: Master “21” (M-20E), Mark “20B”, “20D”, (M20B, M20C), Mooney Statesman (M-20G) Dinfia: Querandi (1A-45) Wassmer: (WA-50) Malmo: Vipan (MF1-10) Cessna Aircraft: Skyhawk O-360-A1D Doyn Aircraft: Doyn-Piper (PA -23 “160”) O-360-A1F6 Cessna Aircraft: Cardinal Cessna Aircraft: Cardinal 177 O-360-A1F6D Teal III: TSC (1A3) O-360-A1G6 Aero Commander O-360-A1G6D Beech Aircraft: Duchess 76 O-360-A1H6 Piper Aircraft: Seminole (PA-44) 12 O-360-A1LD Wassmer: Europa WA-52 O-360-A1P Aviat: Husky Center Est Aeronautique: Regente (DR-253) S.O.C.A.T.A.: Rallye Commodore (MS-893) Societe Aeronautique Normande: Mousquetaire (D-140) Bolkow: Klemm (K1-107C) Partenavia: Oscar (P-66) O-360-A2A Beagle: Husky (D5-180) (J1-U) Piper Aircraft: Comanche (PA-24), Cherokee “C” (PA-28 “180”) O-360-A2D Mooney Aircraft: Master “21” (M-20D), Mark “21” (M-20E) O-360-A2E Std. Helicopter Aero Commander: Lark (100) O-360-A2F Cessna Aircraft: Cardinal O-360-A2G Beech Aircraft: Sport C.A.A.R.P.S.A.N.: (M-23III) Societe Aeronautique Normande: Jodel (D-140C) Robin: Regent (DR400/180), Remorqueur (DR400/180R). R-3170 S.O.C.A.T.A.: Rallye 180GT, Sportavia Sportsman (RS-180) Norman Aeroplace Co.: NAC-1 Freelance O-360-A3A Nash Aircraft Ltd.: Petrel S.O.C.A.T.A.: TB-10 O-360-A3AD Robin: Aiglon (R-1180T) O-360-A4A Piper Aircraft: Cherokee “D” (PA-28 “180”) O-360-A4D Varga: Kachina O-360-A4G Beech Aircraft: Musketeer Custom III Grumman American: Tiger O-360-A4K Beech Aircraft: Sundowner 180 Piper Aircraft: Archer II (PA-28 “18”) O-360-A4M Valmet: PIK-23 O-360-A4N Cessna Aircraft: 172 (Optional) O-360-A4P Penn Yan: Super Cub Conversion O-360-A5AD C. Itoh and Co.: Fuji FA -200 O-360-B2C Seabird Aviation: SB7L O-360-C1A Intermountain Mfg. Co.: Call Air (A-6) O-360-C1E Bellanca Aircraft: Scout (8GCBC-CS) 13 O-360-C1F Maule: Star Rocket MX-7-180 O-360-C1G Christen: Husky (A-1) O-360-C2B Hughes Tool Co.: (269A) O-360-C2D Hughes Tool Co.: (269A) Hughes Tool Co.: (YHO-2HU) Military O-360-C2E Bellanca Aircraft: Scout (8GCBC FP) O-360-C4F Maule: MX-7-180A O-360-C4P Penn Yan: Super Cub Conversion O-360-F1A6 Cessna Aircraft: Cutlass RG O-360-J2A Robinson: R22 Beech Aircraft: Travel-Air (B-95A) IO-360-B1A Doyn Aircraft: Doyn-Piper (PA -23 “200”) Beech Aircraft: Travel-Air (B-95B) Doyn Aircraft: Doyn-Piper (PA -23 “200”) IO-360-B1B Fuji: (FA-200) IO-360-B1D United Consultants: See-Bee IO-360-B1E Piper Aircraft: Arrow (PA-28 “180R”) IO-360-B1F Utva: 75 IO-360-B2E C.A.A.R.P. C.A.P. (10) IO-360-B1F6 Great Lakes: Trainer IO-360-B1G6 American Blimp: Spector 42 IO-360-B2F6 Great Lakes: Trainer LO-360-A1G6D Beech Aircraft: Duchess LO-360-A1H6 Piper Aircraft: Seminole (PA-44) IO-360-E1A T.R. Smith Aircraft: Aerostar IO-360-L2A Cessna Aircraft: Skyhawk C-172 IO-360-M1A Diamond Aircraft: DA-40 Vans Aircraft: RV6, RV7, RV8 IO-360-M1B Lancair: 360 F.F.A.: Bravo (200) AEIO-360-B1F Grob: G115/Sport-Acro AEIO-360-B1G6 Great Lakes AEIO-360-B2F Mundry: CAP-10 AEIO-360-B4A Pitts: S-1S AEIO-360-H1A Bellanca Aircraft: Super Decathalon (8KCAB-180) 14 AEIO-360-H1B American Champion: Super Decathalon VO-360-A1A Brantly Hynes Helicopter: (B-2) VO-360-A1B Brantly Hynes Helicopter: (B-2, B2-A). Military (YHO-3BR) VO-360-B1A Brantly Hynes Helicopter: (B-2, B2-A) IVO-360-A1A Brantly Hynes Helicopter: (B2-B) HO-360-B1A Hughes Tool Co.: (269A) HO-360-B1B Hughes Tool Co.: (269A) HO-360-C1A Schweizer: (300C) HIO-360-B1A Hughes Tool Co.: Military (269-A-1). (TH-55A) HIO-360-B1B Hughes Tool Co.: (269A) HIO-360-G1A Schweizer: (CB) O-540-A1A Rhein-Flugzeugbau: (RF-1) Piper Aircraft: Comanche (PA-24 “180”) Helio: Military (H-250) O-540-A1A5 Yoeman Aviation: (YA-1) O-540-A1B5 Piper Aircraft: Aztec (PA-23 “250”), Comanche (PA-24 “250”) O-540-A1C5 Piper Aircraft: Comanche (PA-24 “250”) Found Bros.: (FBA-2C) O-540-A1D Dornier: (DO-28-B1) Piper Aircraft: Aztec (PA-23 “250”), Comanche (PA-24 “250”), Military Aztec (U-11A) O-540-A1D5 Dornier: (DO-28) Aero Commander: (500) O-540-A2B Mid-States Mfg. Co.: Twin Courier (H-500), (U-5) O-540-A3D5 Piper Aircraft: Navy Aztec (PA-23 “250”) O-540-B1A5 Piper Aircraft: Apache (PA-23 “235”) Piper Aircraft: Comanche (PA-24 “250”) O-540-B1B5 Doyn Aircraft: Doyn-Piper (PA-24 “250”) O-540-B1D5 Wassmer: (WA-421) Piper Aircraft: Pawnee (PA-25 “235”), Cherokee (PA -28 “235”), Aztec (PA - 23 “235”) Intermountain Mfg. Co.: Call Air (A-9) Rawdon Bros.: Rawdon (T-1) O-540-B2B5 S.O.C.A.T.A.: Rallye 235CA O-540-B2C5 Piper Aircraft: Pawnee (PA-25 “235”) 15 Piper Aircraft: Cherokee (PA-28 “235”) Embraer: Corioca (EMB-710) S.O.C.A.T.A.: Rallye 235GT, Rallye 235C O-540-B4B5 Maule: Star Rocket (MX-7-235), Super Rocket (M-6-235), Super Std. Rocket (M-7-235) Piper Aircraft: Comanche (PA-24 “260”) Aviamilano: Flamingo (F-250) O-540-E4A5 Siai-Marchetti: (SF-260), (SF-208) Britten-Norman: (BN-2) O-540-E4B5 Piper Aircraft: Cherokee Six (PA-32 “260”) O-540-E4C5 Pilatus Britten-Norman: Islander (BN-2A-26), Islander (BN-2A-27), Islander II (BN-2B-26), Islander (BN-2A-21), Trislander (BN-2A-Mark III-2) Omega Aircraft: (BS-12D1) O-540-F1B5 Robinson: (R-44) O-540-G1A5 Piper Aircraft: Pawnee (PA -25 “260”) O-540-H1B5D Aero Boero: 260 Embraer: Impanema “AG” O-540-H2A5 Gippsland: GA-200 O-540-H2B5D Aero Boero: 260 O-540-J1A5D Maule: Star Rocket (MX-7-235), Super Rocket (M-6-235), Super Std. Rocket (M-7-235) O-540-J3A5 Robin: R-3000/235 O-540-J3A5D Piper Aircraft: Dakota (PA -28-236) O-540-J3C5D Cessna Aircraft: Skylane RG O-540-L3C5D Cessna Aircraft: TR-182, Turbo Skylane RG IO-540-C1B5 Piper Aircraft: Aztec B (PA-23 “250”), Comanche (PA-24 “250”) IO-540-C1C5 Riley Aircraft: Turbo-Rocket Piper Aircraft: Aztec C (PA-23 “250”), Aztec F Wassmer: (WA4-21) Avions Pierre Robin: (HR100/250) Bellanca Aircraft: Aries T-250 IO-540-C4B5 Aerofab: Renegade 250 IO-540-C4D5 S.O.C.A.T.A.: TB-20 IO-540-C4D5D S.O.C.A.T.A.: Trinidad TB-20 Piper Aircraft: Comanche (PA-24 “260”) IO-540-D4A5 Siai-Marchetti: (SF-260) 16 IO-540-D4B5 Cerva: (CE-43 Guepard) IO-540-J4A5 Piper Aircraft: Aztec (PA-23 “250”) IO-540-R1A5 Piper Aircraft: Comanche (PA-24) IO-540-T4A5D General Aviation: Model 114 IO-540-T4B5 Commander: 114B IO-540-T4B5D Rockwell: 114 IO-540-T4C5D Lake Aircraft: Seawolf Maule: MT-7-260, M -7-260 IO-540-V4A5 Aircraft Manufacturing Factory IO-540-V4A5D Brooklands: Scoutmaster IO-540-W1A5 Maule: MX-7-235, MT-7-235, M7-235 IO-540-W1A5D Maule: Star Rocket (MX-7-235), Super Rocket (M-6-235), Super Std. Rocket (M-7-235) IO-540-W3A5D Schweizer: Power Glider Christen: Pitts (S-2S), S-2B) Siai-Marchetti: SF-260 H.A.L.: HPT-32 AEIO-540-D4A5 Slingsby: Firefly T3A Moravan: Zlin-50L AEIO-540-D4B5 H.A.L.: HPT-32 AEIO-540-D4D5 Burkhart Grob: Grob G, 115T Aero TIO-540-C1A Piper Aircraft: Turbo Aztec (PA-23-250) TIO-540-K1AD Piper Aircraft TIO-540-AA1AD Aerofab Inc.: Turbo Renegade (270) TIO-540-AB1AD S.O.C.A.T.A.: Trinidad TC TB-21 TIO-540-AB1BD Schweizer TIO-540-AF1A Mooney Aircraft: “TLS” M20M TIO-540-AG1A Commander Aircraft: 114TC TIO-540-AK1A Cessna Aircraft: Turbo Skylane T182T LTIO-540-K1AD Piper Aircraft Unsafe Condition (d) This AD results from reports of 45 failures with head separations of ECi cylinder assemblies. We are issuing this AD to prevent loss of engine power due to cracks at the head-to-barrel interface in the cylinder assemblies and possible engine failure caused by separation of a cylinder head, which could result in loss of control of the aircraft. 17 Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. Engines Not Overhauled or Cylinder Assemblies Not Replaced Since New (f) If your engine has not been overhauled or had any cylinder assemblies replaced since new, no further action is required. Engines Overhauled or Cylinder Assemblies Replaced Since New (g) If your engine was overhauled or had a cylinder assembly replaced since new, do the following: (1) Before further flight, inspect the maintenance records and engine logbook to determine if the overhaul or repair facility used ECi cylinder assemblies, P/N AEL65102, with cylinder head, PN AEL85099, with a SN 1138-02 through SN 35171-22, or a SN 35239-01 through SN 37016-28, installed. (2) If the cylinder assemblies are not ECi, P/N AEL65102, no further action is required. (3) If the cylinder assemblies are ECi, P/N AEL65102, and if the serial number is not listed in this AD, no further action is required. (4) If the cylinder assemblies are ECi, P/N AEL65102, and if the serial number is listed in this AD, do the following: Group ''A'' Cylinder Assemblies (i) For Group ''A'' cylinder assemblies: (A) Perform an initial visual inspection as specified in paragraphs (h) through (j) of this AD, and an initial compression test as specified in paragraphs (k) through (o) of this AD, within the next 10 operating hours time-in-service (TIS), if the cylinder assembly has 350 or more operating hours TIS on the effective date of this AD, but fewer than 2,000 operating hours TIS. (B) Perform an initial visual inspection as specified in paragraphs (h) through (j) of this AD, and an initial compression test as specified in paragraphs (k) through (o) of this AD, before exceeding 350 operating hours TIS, if the cylinder assembly has fewer than 350 operating hours TIS on the effective date of this AD. (C) Replace cylinder assemblies installed in helicopter engines within the next 25 operating hours TIS after the effective date of this AD if the cylinder assembly has 1,500 operating hours TIS or more on the effective date of this AD. (D) Replace cylinder assemblies installed in airplane engines within the next 25 operating hours TIS after the effective date of this AD if the cylinder assembly has 2,000 operating hours TIS or more on the effective date of this AD. (E) Perform repetitive visual inspections as specified in paragraphs (h) through (j) of this AD, and repetitive compression tests as specified in paragraphs (k) through (o) of this AD, within every 50 operating hours TIS. (F) Replace cylinder assemblies installed in helicopter engines that pass the visual inspections and compression tests, no later than 1,500 operating hours TIS after the effective date of this AD. (G) Replace cylinder assemblies installed in airplane engines that pass the visual inspections and compression tests, no later than 2,000 operating hours TIS after the effective date of this AD. Group ''B'' Cylinder Assemblies (ii) For Group ''B'' cylinder assemblies: 18 (A) Perform an initial visual inspection as specified in paragraphs (h) through (j) of this AD, and initial compression test as specified in paragraphs (k) through (o) of this AD, within an additional 10 operating hours TIS. (B) Replace the cylinder assembly within the next 25 operating hours TIS after the effective date of this AD if the cylinder assembly has 350 or more operating hours TIS on the effective date of this AD. (C) Replace cylinder assemblies that pass the initial visual inspections and compression tests, before exceeding 350 operating hours TIS after the effective date of this AD. Visual Inspection (h) Visually inspect around the exhaust valve side, for cracks or any signs of black or white residue of combustion leakage from cracks. (i) Replace cracked cylinder assemblies before further flight. (j) Information on cylinder assembly visual inspection can be found in ECi Mandatory Service Bulletin (MSB) No. 08-1, Revision 3, dated August 19, 2008. Cylinder Assembly Compression Test (k) Compression test the cylinder assembly. (l) Information on cylinder assembly compression testing can be found in ECi MSB No. 08-1, Revision 3, dated August 19, 2008. (m) During the compression test, if the cylinder pressure gauge reads below 70 pounds-per- square-inch, apply a water and soap solution to the side of the leaking cylinder, near the head-to- barrel interface. (n) Replace the cylinder assembly before further flight, if air leakage and bubbles are observed on the side of the cylinder assembly, near the head-to-barrel interface. (o) Repair or replace the engine cylinder assembly before further flight if the cause of the low gauge reading in paragraph (m) of this AD is from leaking intake or exhaust valves, or from leaking piston rings. Prohibition of ECi Cylinder Assemblies Affected by This AD (p) After the effective date of this AD, do not install any ECi cylinder assembly, P/N AEL65102, with cylinder head, P/N AEL85099, and with SN 1138-02 through SN 35171-22, or SN 35239-01 through SN 37016-28, onto any engine, and do not attempt to repair or reuse these ECi cylinder assemblies. Alternative Methods of Compliance (q) The Manager, Special Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. 19 Special Flight Permits (r) Under 14 CFR 39.23, we will not approve special flight permits for this AD for engines that have failed the visual inspection or the cylinder assembly compression test required by this AD. Related Information (s) ECi Mandatory Service Bulletin No. 08-1, Revision 3, dated August 19, 2008, pertains to the subject of this AD. (t) Contact Peter W. Hakala, Aerospace Engineer, Special Certification Office, FAA, Rotorcraft Directorate, 2601 Meacham Blvd., Fort Worth, TX 76193; e-mail: peter.w.hakala@faa.gov; telephone (817) 222-5145; fax (817) 222-5785, for more information about this AD. Issued in Burlington, Massachusetts, on September 5, 2008. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E8-21125 Filed 9-12-08; 8:45 am] 1 [Federal Register: December 24, 2008 (Volume 73, Number 248)] [Rules and Regulations] [Page 78939-78944] From the Federal Register Online via GPO Access [wais.access.gpo.gov] [DOCID:fr24de08-8] –––––––––––––––––––––––––––––––––– DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2008-1328; Directorate Identifier 2008-CE-066-AD; Amendment 39-15776; AD 2008-26-10] RIN 2120-AA64 Airworthiness Directives; Cessna Aircraft Company 172, 175, 177, 180, 182, 185, 188, 206, 207, 208, 210, 303, 336, and 337 Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. –––––––––––––––––––––––––––––––––– SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) 172, 175, 177, 180, 182, 185, 188, 206, 207, 208, 210, 303, 336, and 337 series airplanes. This AD requires you to inspect the alternate static air source selector valve to assure that the part number identification placard does not obstruct the alternate static air source selector valve port. If the part number identification placard obstructs the port, this AD also requires you to remove the placard, assure that the port is unobstructed, and report to the FAA if obstruction is found. This AD results from reports of airplanes found with alternate static air source selector valve port obstruction caused by improper installation of the part number identification placard. The actions specified by this AD are intended to prevent erroneous indications from the altimeter, airspeed, and vertical speed indicators, which could cause the pilot to react to incorrect flight information and possibly result in loss of control. DATES: This AD becomes effective on January 5, 2009. On January 5, 2009, the Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD. We must receive any comments on this AD by February 23, 2009. ADDRESSES: Use one of the following addresses to comment on this AD. • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493-2251. • Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590. 2 • Hand Delivery: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. To get the service information identified in this AD, contact Cessna Aircraft Company, P.O. Box 7704, Wichita, Kansas 67277; telephone: (800) 423-7762 or (316) 517-6056; Internet: http://www.cessna.com. To view the comments to this AD, go to http://www.regulations.gov. The docket number is FAA-2008-1328; Directorate Identifier 2008-CE-066-AD. FOR FURTHER INFORMATION CONTACT: Ann Johnson, Aerospace Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: 316- 946-4105; fax: 316-946-4107; e-mail address: ann.johnson@faa.gov. SUPPLEMENTARY INFORMATION: Discussion Reports of improper installation of the part number (P/N) identification placard on P/N 2013142- 18 alternate static air source selector valves prompted us to issue AD 98-01-01, Amendment 39- 10286 (63 FR 3455, January 23, 1998), which applies to certain Cessna Aircraft Company (Cessna) Models 172R and 182S airplanes, and AD 2008-10-02, Amendment 39-155508 (73 FR 24168, May 2, 2008), which applies to certain Cessna 172, 175, 180, 182, 185, 206, 207, 208, 210, and 303 series airplanes. These ADs require inspecting the alternate static air source selector valve to determine if the P/N identification placard obstructs the alternate static air source selector valve port and removing the placard if obstruction is found. These ADs also require reporting to the FAA if obstruction is found. These assemblies are required for flight into instrument flight rules (IFR) conditions as defined in §91.411 of the Federal Aviation Regulations (14 CFR 91.411). Use of these assemblies is optional in visual flight rules (VFR) conditions. After issuing AD 98-01-01 and AD 2008-10-02, we received reports of 15 airplanes not previously affected by either AD with a P/N 2013142-18 installed and the alternate static air source selector valve port was found obstructed by the P/N identification placard. We have been informed that all P/N 2013142-18 alternate static air source selector valves shipped from Cessna Parts Distribution between January 1, 1993, and March 31, 2008, may have port obstruction caused by the P/N identification placard. This condition, if not corrected, could result in the altimeter, airspeed, and vertical speed indicators displaying erroneous indications. This could cause the pilot to react to incorrect flight information and possibly result in loss of control. Relevant Service Information We reviewed Cessna Single Engine Service Bulletin, SB08-34-02, Revision 1, and Cessna Caravan Service Bulletin CAB08-4, Revision 1, both dated October 6, 2008; Cessna Single Engine Service Bulletin SEB08-5 and Cessna Multi-engine Service Bulletin MEB08-6, both dated October 13, 2008. The service information describes procedures for inspecting the alternate static air source selector valve to assure that the P/N identification placard does not obstruct the alternate static air source selector valve port. 3 FAA's Determination and Requirements of This AD We are issuing this AD because we evaluated all the information and determined the unsafe condition described previously is likely to exist or develop on other products of the same type design. This AD requires inspecting the alternate static air source selector valve to assure that the P/N identification placard does not obstruct the alternate static air source selector valve port. If the P/N identification placard obstructs the port, this AD requires you to remove the placard, assure that the port is unobstructed, and report to the FAA if obstruction is found. FAA's Determination of the Effective Date Since an unsafe condition exists that requires the immediate adoption of this AD, we determined that notice and opportunity for public comment before issuing this AD are impracticable, and that good cause exists for making this amendment effective in fewer than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and an opportunity for public comment. We invite you to send any written relevant data, views, or arguments regarding this AD. Send your comments to an address listed under the ADDRESSES section. Include the docket number ''FAA-2008-1328; Directorate Identifier 2008-CE- 066-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the AD. We will consider all comments received by the closing date and may amend the AD in light of those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive concerning this AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ''General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ''significant regulatory action'' under Executive Order 12866; (2) Is not a ''significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. 4 We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. Examining the AD Docket You may examine the AD docket that contains the AD, the regulatory evaluation, any comments received, and other information on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647-5527) is located at the street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39–AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding a new AD to read as follows: 5 FAA Aircraft Certification Service AIRWORTHINESS DIRECTIVE www.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html 2008-26-10 Cessna Aircraft Company: Amendment 39-15776; Docket No. FAA-2008-1328; Directorate Identifier 2008-CE-066-AD. Effective Date (a) This AD becomes effective on January 5, 2009. Affected ADs (b) This AD relates to AD 98-01-01, Amendment 39-10287 and AD 2008-10-02, Amendment 39-15508. These ADs can be found on the Internet at the following Web site: http://rgl.faa.gov/. Applicability (c) This AD applies to all serial numbers (S/Ns) of the airplanes listed in Table 1 of this AD, certificated in any category, that: (1) Were initially delivered from the manufacturer between January 1, 1993, and March 31, 2008, unless the modification/rework required in AD 2008-10-02 has been done and you remain in compliance with that AD; or (2) Have a part number (P/N) 2013142-18 installed as a replacement part anytime after January 1, 1993, unless the modification/rework required in AD 2008-10-02 has been done and you remain in compliance with that AD. Note 1: The affected part was shipped from Cessna Parts Distribution (CPD) between January 1, 1993, and March 31, 2008. Note 2: P/N 2013142-18 replaced P/Ns 2013142-9, -13, and -17. Table 1. – Applicable Airplane Models Models 172 F172K 177 172A F172L 177A 172B F172M 177B 172C F172N 177RG 172D F172P F177RG 172E FR172E 180 172F (USAF T-41A) FR172F 180A 172G FR172G 180B 172H (USAF T-41A) FR172H 180C 172I FR172J 180D 172K FR172K 180E 172L P172D 180F 6 172M R172E (USAF T-41B), (USAF T-41C and D) 180G 172N R172F (USAF T-41) 180H 172P R172G (USAF T-41C or D) 180J 172Q R172H (USAF T-41D) 180K 172R R172J 182 172S R172K 182A F172D 172RG 182B F172E 175 182C F172F 175A 182D F172G 175B 182E F172H 175C 182F 182G A185F U206D 182H 206 U206E 182J 206H U206F 182K P206 U206G 182L P206A 207 182M P206B 207A 182N P206C T207 182P P206D T207A 182Q P206E 208 182R T206H 208B 182S TP206A 210 182T TP206B 210A F182P TP206C 210B F182Q TP206D 210C FR182 TP206E 210D R182 TU206A 210E T182 TU206B 210F T182T TU206C 210G TR182 TU206D 210H 185 TU206E 210J 185A TU206F 210K 185B TU206G 210L 185C U206 210M 185D U206A 210N 185E U206B 210R A185E U206C 210-5 (205) 210-5A (205A) FT337F T210F M337B (USAF 02A) T210G T337B T210H T337C T210J T337D T210K T337E T210L T337F T210M T337H T210N T337H-SP T210R T303 7 336 337 337A (USAF 02B) 337B 337C 337D 337E 337F 337G 337H F337E F337F F337G F337H FT337E Unsafe Condition (e) This AD is the result of reports of improper installation of the part number identification placard on the alternate static air source selector valve. We are issuing this AD to prevent erroneous indications from the altimeter, airspeed, and vertical speed indicators, which could cause the pilot to react to incorrect flight information and possibly result in loss of control. Compliance (e) To address this problem, you must do the following, unless already done. A person authorized to perform maintenance as specified in 14 CFR section 43.3 of the Federal Aviation Administration Regulations (14 CFR 43.3) is required to do all the actions required in this AD. Actions Compliance Procedures (1) For all affected airplanes that are not equipped for flight under instrument flight rules (IFR): Inspect the alternate static air source selector valve to assure that the part number identification placard is not obstructing the port. Within the next 100 hours time-in-service (TIS) after January 5, 2009 (the effective date of this AD) or within the next 4 months after January 5, 2009 (the effective date of this AD), whichever occurs first. Following the procedures in Cessna Single Engine Service Bulletin SB08-34-02, Revision 1, dated October 6, 2008; Cessna Caravan Service Bulletin CAB08-4, Revision 1, dated October 6, 2008; Cessna Single Engine Service Bulletin SEB08-5, dated October 13, 2008; or Cessna Multi-engine Service Bulletin MEB08-6, dated October 13, 2008, as applicable. 8 (2) For all affected airplanes that are equipped for flight under instrument flight rules (IFR): (i) Inspect the alternate static air source selector valve to assure that the part number identification placard is not obstructing the port; or (ii) Fabricate a placard that incorporates the following words (using at least 1/8-inch letters) and install this placard on the instrument panel within the pilot’s clear view: “IFR OPERATION IS PROHIBITED” and “USE OF THE ALTERNATE STATIC AIR SOURCE IS PROHIBITED.” (A) Inspect within the next 10 days after January 5, 2009 (the effective date of this AD); or (B) Install placards before further flight after January 5, 2009 (the effective date of this AD). Following the procedures in Cessna Single Engine Service Bulletin SB08-34-02, Revision 1, dated October 6, 2008; Cessna Caravan Service Bulletin CAB08-4, Revision 1, dated October 6, 2008; Cessna Single Engine Service Bulletin SEB08-5, dated October 13, 2008; or Cessna Multi-engine Service Bulletin MEB08-6, dated October 13, 2008, as applicable. (3) For all affected airplanes that are equipped for flight under instrument flight rules (IFR): If placards were installed in accordance with paragraph (e)(2)(ii) of this AD, inspect the alternate static air source selector valve to assure that the part number identification placard is not obstructing the port. Within the next 100 hours TIS after January 5, 2009 (the effective date of this AD) or within the next 4 months after January 5, 2009 (the effective date of this AD), whichever occurs first. After doing the inspection, remove the placards installed in accordance with paragraph (e)(2)(ii) of this AD before further flight. Following the procedures in Cessna Single Engine Service Bulletin SB08-34-02, Revision 1, dated October 6, 2008; Cessna Caravan Service Bulletin CAB08-4, Revision 1, dated October 6, 2008; Cessna Single Engine Service Bulletin SEB08-5, dated October 13, 2008; or Cessna Multi-engine Service Bulletin MEB08-6, dated October 13, 2008, as applicable. (4) For all affected airplanes: If the alternate static air source selector valve port is found obstructed by the part number identification placard during the inspection required in paragraphs (e)(1), (e)(2)(i), and (e)(3) of this AD, remove the placard from the valve body, discard the placard, and assure that the port is open and unobstructed. Before further flight after the inspection required in paragraphs (e)(1), (e)(2)(i), and (e)(3) of this AD. Following the procedures in Cessna Single Engine Service Bulletin SB08-34-02, Revision 1, dated October 6, 2008; Cessna Caravan Service Bulletin CAB08-04, Revision 1, dated October 6, 2008; Cessna Single Engine Service Bulletin SEB08-5, dated October 13, 2008; or Cessna Multi-engine Service Bulletin MEB08-6, dated October 13, 2008, as applicable. 9 (5) For all affected airplanes: When a replacement valve is needed, only install a P/N 2013142-18 alternate static air source selector valve that has been inspected and the port is found free from obstruction. As of 10 days after January 5, 2009 (the effective date of this AD). A person authorized to perform maintenance as specified in 14 CFR section 43.3 of the Federal Aviation Administration Regulations (14 CFR 43.3) is required to do the inspection. (f) Report to the FAA the results of the inspection required by this AD where an obstruction was found. (1) Submit this report within 10 days after the inspection or 10 days after the effective date of this AD, whichever occurs later. (2) Use the form in Figure 1 of this AD and submit it to FAA, Manufacturing Inspection District Office, Mid-Continent Airport, 1804 Airport Road, Room 101, Wichita, Kansas 67209; or fax to (316) 946-4189. (3) The Office of Management and Budget (OMB) approved the information collection requirements contained in this regulation under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and assigned OMB Control Number 2120-0056. Figure 1 10 Alternative Methods of Compliance (AMOCs) (g) The Manager, Wichita Aircraft Certification Office (ACO), 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: Ann Johnson, Aerospace Engineer, FAA, Wichita ACO, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: 316-946-4105; fax: 316-946-4107; e-mail address: ann.johnson@faa.gov. 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. (h) AMOCs approved for AD 2008-10-02 are approved for this AD. Material Incorporated by Reference (i) You must use Cessna Single Engine Service Bulletin, SB08-34-02, Revision 1, dated October 6, 2008; Cessna Caravan Service Bulletin CAB08-4, Revision 1, dated October 6, 2008; Cessna Single Engine Service Bulletin SEB08-5, dated October 13, 2008; and Cessna Multi-engine Service Bulletin MEB08-6, dated October 13, 2008, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Cessna Aircraft Company, P.O. Box 7704, Wichita, Kansas 67277; telephone: (800) 423-7762 or (316) 517-6056; Internet: http://www.cessna.com. (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; 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/code_of_federal_regulations/ibr_locations.html. Issued in Kansas City, Missouri, on December 15, 2008. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service.