Airworthiness Directives; Cessna Models 170A, 170B, 172, 172A through 172P, 175, 175A, 175B, 175C, P172D and R172E (USAF T-41B) Airplanes

11034; February 26,1979) and certifies that it will not have a significant economic impact on a substantial number of small entities under the criteria of the Regulatory Flexibility Act since it involves inspections and repairs on only a few aircraft owned by small entities. A final evaluation has been prepared for this regulation and has been placed in the docket A copy of it may be obtained by contacting the person identified under the caption “ FOR FURTHER INFORMATION CONTACT.” This rule is a final order of the Administrator under the Federal Aviation Act of 1958, as amended. As such, it is subject to review only by the courts of appeals of the United States, or the United States Court of Appeals for the District of Columbia. Issued in Washington, D.C., on March 23, 1982. M. C. Beard, Director o f Airworthiness. [FR Doc. 82-8818 Filed 3-31-82; 8:45 am] BILLING CODE 4910-13-M 14 CFR Part 39 [Docket No. 82-C E-9-A D ; Arndt 39-4353] Airworthiness Directives; Cessna Models 170A, 170B, 1 72 ,172A through 172P, 1 75 ,175A, 175B, 175C, P172D and R172E (USAF T-41B) Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. 13786 Federal Register / Vol. 47, No. 63 / Thursday, April 1, 1982 / Rules and Regulations SUMMARY: This amendment adds a new Airworthiness Directive (AD) applicable to those Cessna Models 170A, 170B, 172, 172A through 172P, 175,175A, 175B, 175C, P172D and R172E (USAF T-41B) airplanes modified to include 150 through 180 horsepower Lycoming engines in accordance with Supplemental Type Certificates (STC) SA3-13, SA3-126, SA3-571, SA3-672, SA3-674, SA135CE, SA420CE, SA421CE, SA424CE, SA610SW, SA647CE, SA777CE, SA806CE, SA807CE or SA1324CE, respectively. This AD requires a one-time inspection and, if necessary, modification of the engine crankcase breather tube to incorporate an acceptable alternate vent. This action is necessary to prevent complete vent blockage if the exit is obstructed by ice. Ice blockage of this vent may increase engine crankcase pressure to a level that will cause the front crankcase seal to be forced out, Which may result in loss of engine oil and engine failure. DATES: Effective Date: April 8,1982. COMPLIANCE: Within 50 hours time-in service after the effective date of this AD. FOR FURTHER INFORMATION CONTACT: Paul O. Pendleton, Aerospace Engineer, Wichita Aircraft Certification Office, Room 238, Terminal Building No. 2299, Mid-Continent Airport, Wichita, Kansas 67209; Telephone (316) 269-7010. SUPPLEMENTARY INFORMATION: An incident occurred wherein there was ice blockage of the engine crankcase breather vent exit on Cessna Models 170B and R172E airplanes equipped with a 180-horsepower Lycoming engine per a Supplemental Type Certificate. Subsequent investigation disclosed that some Cessna Models 170A, 170B, 172, 172A through 172P, 175,175A, 175B, 175C, P172D and R172E (USAF T-41B) airplanes modified in accordance with STCs SA13, SA3-126, SA3-571, SA3-672, SA3-674, SA135CE, SA420CE, SA421CE, SA424CE, SA610SW, SA647CE, SA777CE, SA806CE, SA807CE or SA1324CE may not have necessary alternate vent provisions in the engine crankcase breather system. Examination of the data disclosed that some of these STCs require incorporation of an alternate engine crankcase breather outlet while others do not. On those STCs not having this provision, the breather outlet was protected from freezing over due to the proximity of the hot engine exhaust outlet. Subsequently, the engine exhaust system was redesigned and the exhaust outlet was moved to the opposite side of the cowling. This left the crankcase breather unprotected on those airplanes equipped with the redesigned engine exhaust system. The original exhaust system is no longer available from any of the STC owners that are currently manufacturing parts. Therefore, some airplanes with the original exhaust system have had it replaced with the redesigned exhaust system. More of the original exhaust systems will be replaced as they reach their service life. Since the condition described herein may result in loss of engine oil and engine failure, and may exist on other airplanes of the same type design, the FAA is issuing an AD, applicable to the airplanes set forth above. It requires inspection of the existing engine crankcase breather vent, and modification, when necessary, to incorporate an alternate engine crankcase breather outlet (hole drilled in tube) to prevent breather obstruction by ice at the outlet. The FAA has determined that there is an immediate need for this regulation to assure safe operation of the affected airplanes. Therefore, notice and public procedure under 5 U.S.C. 553(b) is impracticable and contrary to the public interest, and good cause exists for making this admendment effective in less than thirty (30) days after the date of publication in the Federal Register. Adoption of the Amendment Accordingly and pursuant to the authority delegated to me by the Administrator, § 39.13 of Part 39 of the Federal Aviation Regulations (14 CFR 39.13) is amended by adding the following new Airworthiness Directive. CESSNA: Applies to Models 170A, 170B, 172, 172A through 172P, 175,175A, 175B, 175C, P172D, and R172E (USAF T-41B) airplanes modified in accordance with STCs SA3-13, SA3-126, SA3-571, SA3- 672, SA3-674, SA135CE, SA420CE, SA421CE, SA424CE, SA610SW, SA647CE, SA777CE, SA806CE, SA807CE, or SA1324CE, certificated in any category. Compliance: required as indicated, unless already accomplished. To reduce the possibility of rapid loss of engine oil caused by ice obstruction of the engine crankcase breather, accomplish the following: (A) Within the next 50 hours time-in service after the effective date of this AD. 1. Visually examine the engine crankcase breather to determine if an alternate air outlet is drilled or cut in the tube as shown in Figure 1. If any of these provisions exist, make an appropriate entry in the aircraft maintenance records per paragraph (B). No further action is necessary. 2. If the hole or cutout shown in Figure 1 is not in the engine crankcase breather tube: a. Inspect the crankcase to crankshaft seal and ensure that the seal is secure. (This seal is located behind the starter ring gear in the forward most part of the crankcase.) Reinstall or replace this seal if it is not flush with the forward face of the crankcase. b. Drill the engine crankcase breather tube line to include an alternate air outlet as shown in Figure 1. (B) Paragraph (A)l of this AD may be accomplished by the holder of at least a private pilot certificate issued under Part 61 of the Federal Aviation Regulations on any airplane owned or operated by that person. Make the prescribed entry in the aircraft maintenance records, including those airplanes on which it has already been accomplished, indicating compliance with this AD. (C) The airplane may be flown in accordance with FAR 21.197 to a location where paragraph (A)2 of this AD may be accomplished. (D) Any equivalent method of compliance with this AD may be used when approved by the Chief, Wichita Aircraft Certification Office, FAA, Room 238, Mid-Continent Airport, Terminal Building No. 2299., Wichita, Kansas 67209; Telephone (316) 269-7000. This amendment becomes effective on April 8,1982. (Secs. 313(a), 601 and 603 of the Federal Aviation Act of 1958, as amended (49 U.S.C. 1354(a), 1421 and 1423);. sec. 6(c) Department of Transportation Act (49 U.S.C. 1655(c)); § 11.89 of the Federal Aviation Regulations (14 CFR 11.89)) Note.—The FAA has determined that this regulation involves an emergency regulation which is not considered to be major under Executive Order 12291 or significant under DOT Regulatory Policies and Procedures (44 FR11034; February 28,1979), and certifies that the rule will not have a significant economic impact on a substantial number of small entities under the criteria of the Regulatory Flexibility Act since it involves inspection and modifications applicable to only a few aircraft owned by small entities. If this action is subsequently determined to involve a significant regulation, a final regulatory evaluation or analysis, as appropriate, will be prepared and placed in the regulatory docket; otherwise, an evaluation is not required. This is a final order of the Administrator under the Federal Aviation Act of 1958, as amended. As such, it is subject to review by only the Courts of Appeals of the United States or the United States Court of Appeals of the District of Columbia. Issued in Kansas City, Missouri, on March 19,1982. John E. Shaw, Acting Director, Central Region. BILLING CODE 4910-13-M Federal Register / Vol. 47, No. 63 / Thursday, April 1, 1982 / Rules and Regulations 13787 TYPICAL INSTALLATION V v A ^ l j? \ fÀ 1. BREAT H E R TUBE 2. ICE HOLE 3. HOSE (TO ENGINE) k. L Y C O M I N G ENGINE 5. PROPELLER 6. A I R FILTER 7. EXHAUST PIPE 8. LOWER COWL LIP 9. ENGINE.MOUNT 10. FIREWALL PREVIOUS Accepted methods 3 « *n» 9 * m o * Bottom of t u b e o k W HEN ALREADY C /W W V W r I m fsl H o s e 0 — 0 Tp r i l l h o l e b e t w e e n io” i 9 * up FROM Bottom op TUBE. FIGURE I BREATHER t u b e assy. £ I C E ^ HOLE ( d r ill Fh *C 2S ) p i a .) A W W J 0 J F A / CAUTION0^ Bottom e n d of b r e a t h e r t u r e w a r TO CVrtND BELOW Lower cowl Lip . ( see T T f « ® «h PIO above) [PR Doc. 82-8590 Filed 3-31-82; 8:45 am] BILLING CODE 4 9 1 0 -1 3 -C 13788 Federal Register / Vol. 47, No. 63 / Thursday, April 1, 1982 / Rules an d Regulations 14 CFR Part 39 [Docket No. 82-CE-12-AD; Arndt. 39-4355] Airworthiness Directives; Schweizer G-164 Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. a c t io n : Final rule. SUMMARY: This Airworthiness Directive (AD), applicable to Schweizer G-164 series airplanes, requires modification of the fuel shut-off valve installation to incorporate a positive stop. This will prevent over-rotation of the fuel shut-off valve to an unplacarded “OFF” position which may result in engine fuel starvation. EFFECTIVE DATE: April 6, 1982. Compliance: Within 100 hours time-in service after the effective date of this AD. ADDRESSES: Schweizer Ag-Cat Service Bulletin No. 78 dated January 26,1982, applicable to this AD, may be obtained from Schweizer Aircraft Corporation, P.O. Box 147, Elmira, New York 14902 or may be examined at the FAA New York Aircraft Certification Office, Federal Building, JFK International Airport, Jamaica, New York 11430. A copy of it is also contained in the Rules Docket, Office of the Regional Counsel, FAA, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. FOR FURTHER INFORMATION CONTACT: Mr. L. Lipsius, Propulsion Section, ANE- 174, New York Aircraft Certification Office, Federal Building, JFK International Airport, Jamaica, New York 11430; Telephone (212) 995-2894. SUPPLEMENTARY INFORMATION: It has been determined on Schweizer G-164 series airplanes that a large clockwise force on the fuel shut-off valve handle, when in the “ON” position, may deflect the existing stop sufficiently to allow the valve to rotate past the stop to an unplacarded “OFF” position. The manufacturer has issued Schweizer Ag- Cat Service Bulletin No. 78, dated January 26,1982, which provides instructions for the incorporation of an improved positive fuel shut-off valve stop to prevent this occurrence. If this occurs, the pilot may be confused as to the actual position of the fuel shut-off valve, and engine fuel starvation will result. This loss of engine power could cause an accident. Since the condition described herein is likely to exist or develop in other airplanes of the same type design, an AD is being issued, applicable to Schweizer G-164 series airplanes, making compliance with the aforementioned service bulletin mandatory. Because a potentially hazardous condition exists that requires the immediate adoption of this regulation, it is found that notice and public procedure hereon are impractical and good cause exists for making this airworthiness directive effective in less than thirty (30) days. Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, § 39.13 of Part 39 of the Federal Aviation Regulations (14 CFR 39.13) is amended by adding the following new AD: Schweizer: Applies to Model G-184A (S/Ns 1726A through 1730A); Model G-164B (S/ N 335B through 659B); Model G-164C (S/ N 1C through 44C); and Model G-164D (S/N 1 D through 22D) airplanes certificated in any category. Compliance required as indicated, unless already accomplished. To assure a positive stop of the fuel shut off valve at the “ON” position, within the next 100 hours time-in-service after the effective date of this AD, accomplish the following: (a) Modify the fuel shut-off valve control by installation of a new stop-plate, P/N A1552- 71, in accordance with instructions in Schweizer Ag-Cat Service Bulletin No. 78 dated January 26,1982. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) Any equivalent method of compliance with this AD, when used, must be approved by the Chief, New York Aircraft Certification Office, FAA, Eastern Region, Federal Building, JFK International Airport, Jamaica, New York 11430; Telephone (212) 995-2842. This amendment becomes effective on Aprils, 1982. (Secs. 313(a), 601, and 603 of the Federal Aviation Act of 1958, as amended (49 U.S.C. 1354(a), 1421, and 1423); sec. 6(c), Department of Transportation Act (49 U.S.C. 1655(c)); § 11.89 of the Federal Aviation Regulations (14 CFR 11.89)) Note.—The FAA has determined that this regulation involves an emergency regulation which is not considered to be major under Executive Order 12291 or significant under DOT Regulatory Policies and Procedures (44 FR11034; February 26,1979), and certifies that the rule will not have a significant economic impact on a substantial number of small entities under the criteria of the Regulatory Flexibility Act since it involves a modification to only a few aircraft owned by small entities. If this action is subsequently determined to involve a significant regulation, a final regulatory evaluation or analysis, as appropriate, will be prepared and placed in the regulatory docket; otherwise, an evaluation is not required. A copy of it, when filed, may be obtained by contacting the rules docket at the location identified under the caption “ADDRESSES.” This is a final order of the Administrator under the Federal Aviation Act of 1958, as amended. As such, it is subject to review by only the Courts of Appeals of the United States or the United States Court of Appeals of the District of Columbia Issued in Kansas City, Missouri, on March 22,1982. John E. Shaw, Acting Director, Central Region. [FR Doc. 82-8591 Filed 3-31-82; 8:45 am] BILLING CODE 4910-13-M 14 CFR Part 39 [Docket No. 82-CE-10-AD ; Amdt. 39-4354] Airworthiness Directives; Janitrol Models B1500, B2030, B3040, and B4050 Combustion Heaters AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final Rule, superseding existing Airworthiness Directive (AD). SUMMARY: This amendment supersedes Airworthiness Directive (AD) 80-09-10 (Amendment 39-3766), and adopts a new AD applicable to Janitrol Models B1500, B2030, B3040, and B4050 combustion heaters. AD 80-09-10 requires repetitive inspections of the heaters at intervals of 100 hours time-in service and overhauls at intervals of 500 hours time-in-service. The heater manufacturer has now developed an improved 100-hour inspection procedure which when used will detect unsafe heaters. Since a satisfactory level of safety will be achieved by this inspection, the mandatory overhaul of the heaters at 500-hour intervals is no longer required. Consequently, this amendment incorporates the improved inspection and relieves owners/ operators of the mandatory heater overhaul. DATE: Effective Date: May 6,1982. Compliance: As prescribed in body of AD. ADDRESSES: Janitrol Aero Division Maintenance and Overhaul Manual Instruction P/N 24E25-1, applicable to this AD, may be obtained from Midland- Ross Corporation, Janitrol Aero Division, 4200 Surface Road, Columbus, Ohio 43228. A copy of it is also contained in the Rules Docket, Office of the Regional Counsel, FAA, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. FOR FURTHER INFORMATION CONTACT: Royace Prather, Chicago Aircraft Certification Office, ACE-140C, FAA, 2300 East Devon Avenue, Des Plaines, Federal Register / Vol. 47, No. 63 / Thursday, April 1, 1982 / Rules and Regulations 13789 Illinois 60018; Telephone number (312) 694-7132. SUPPLEMENTARY INFORMATION: AD 80- 09-10, Amendment 39-3766 (45 FR 29561), applicable to Janitrol Models B1500, B2030, B3040 and B4050 combustion heaters, requires repetitive inspection of these heaters at intervals of 100 hours time-in-service and their overhaul at intervals of 500 hours time- in-service. Subsequent to the issuance of this AD, the heater manufacturer developed an improved inspection procedure which may be relied upon to detect heater deterioration in the incipient or early stage before it results in an unairworthy condition. Heaters inspected in accordance with this improved procedure are not required to be overhauled at 500 hour time-in- service intervals and such heaters may be safely continued in-service until an unsatisfactory condition is indicated by the inspection finding. This inspection procedure is set forth in Janitrol Aero Division Maintenance qnd Overhaul Manual, Instruction P/N 24E25-1 dated October 1981. The regulatory adoption of the improved inspection procedure and discontinuance of these overhauls reduces the burden to the field in maintaining airworthy heaters. Accordingly, a new AD is being issued, superseding AD 80-09-10 applicable to Janitrol Models B1500, B2030, B3040 and B4050 combustion heaters requiring compliance with the aforementioned Janitrol instruction. Since this amendment relieves a restriction and imposes no additional burden on any person, notice and public procedure hereon are unnecessary and good cause exists for making the amendment effective in less than thirty (30) days. ADOPTION OF THE AMENDMENT Accordingly, pursuant to the authority delegated to me by the Administrator, § 39.13 of Part 39 of the Federal Aviation Regulations (14 CFR 39.13) is amended by adding the following new AD: Janitrol Aero Division (Midland-Ross Corporation): Applies to Models B1500, B2030, B3040, and B4050 combustion heaters marked as meeting the standards of FAA TSO-C20, installed in aircraft certificated in any category. Compliance required as indicated, unless already accomplished. To detect and prevent the failure of affected combustion heater tube assemblies, accomplish the following: (a) For installed affected heaters with 450 or more heater-hours time-in-service, since last overhauled or installed new, on the effective date of this AD, comply with paragraph (e) within the next fifty (50) heater- hours time-in-service or twelve (12) months from effective date of this AD, whichever occurs first, and thereafter at intervals not to exceed 100 heater-hours time-in-service or twenty-four (24) months, whichever occurs first. (b) For installed affected heaters with less than 450 heater-hours time-in-service, since last overhauled or installed new, on the effective date of this AD, comply with paragraph (e) before the accumulation of 500 heater-hours time-in-service since last overhauled or installed new, or twelve (12) months from effective date of this AD, whichever occurs first, and thereafter at intervals not to exceed 100 heater-hours time- in-service or twenty-four (24) months, whichever occurs first. (c) For uninstalled out-of-service/ overhauled heaters without a new combustion tube assembly that are installed in aircraft subsequent to the effective date of this AD, comply with paragraph (c) before the accumulation of 250 heater-hours time-in service or twelve (12) months, whichever occurs first, and thereafter at intervals not to exceed 100 heater-hours time-in-service or twenty-four (24) months, whichever occurs first. (d) For uninstalled affected new or overhauled heaters with a new combustion tube assembly that are installed in aircraft subsequent to the effective date of this AD, comply with paragraph (e) before the accumulation of 500 heater-hours time-in- service or twenty-four (24) months, whichever occurs first, and thereafter at intervals not to exceed 100 heater-hours time- in-service or twenty-four (24) months, whichever occurs first. (e) Conduct 100 hour inspection of affected heaters in accordance with Janitrol’s Maintenance and Overhaul Manual, Instruction P/N 24E25-1, dated October 1981. Prior to further flight, overhaul any heater that does not pass the combustion pressure decay test required by this inspection. For all affected Janitrol Aircraft Heaters installed in Cessna or Piper Aircraft, conduct the required overhaul in accordance with the appropriate Cessna or Piper Aircraft Heater Overhaul Manual or Janitrol Overhaul Manual, P/N 24E25-1, dated October 1981. (f) A HEATER HOURMETER may be used to establish heater operating time. If a HEATER HOURMETER is not used, count one (1) heater hour for each two (2) flight hours for normal aircraft flight operation. (g) Upon request of an operator, the Chief, Chicago Aircraft Certification Office, FAA, Central Region, may adjust the compliance time specified in paragraphs (a), (b), (c), and (d) of this AD provided such requests are made through an FAA maintenance inspector, and the request contains substantiating data to justify the request for that operator. (h) An equivalent method of compliance with this AD may be used when approved by the Chief, Chicago Aircraft Certification Office, FAA, 2300 East Devon Avenue, Des Plaines, Illinois 60018, telephone (312) 694- 7357. This AD supersedes AD 80-09-10. This amendment becomes effective May 6,1982. (Secs. 313(a), 601, and 603, Federal Aviation Act of 1958, as amended, (49 U.S.C. 1354(a), 1421, and 1423); sec. 6(c), Department of Transportation Act (49 U.S.C. 1655(c)); and § 11.89 of the Federal Aviation Regulations (14 CFR 11.89). Note.—The FAA has determined that this regulation involves an emergency regulation which is not considered to be major under Executive Order 12291 or significant under DOT Regulatory Policies and Procedures (44 FR 11034; February 26,1979), and certifies that the rule will not have a significant economic impact on a substantial number of small entities under the criteria of the Regulatory Flexibility Act since it involves inspection and overhaul of heaters installed on only a few aircraft owned by small entities. If this action is subsequently determined to involve a significant regulation, a final regulatory evaluation or analysis, as appropriate, will be prepared and placed in the regulatory docket; otherwise, an evaluation is not required. A copy of it, when filed, may be obtained by contacting the rules docket at the location identified under the caption “ADDRESSES.” This is a final order of the Administrator under the Federal Aviation Act of 1958, as amended. As such, it is subject to review by only the Courts of Appeals of the United States or the United States Court of Appeals of the District of Columbia. Issued in Kansas City, Missouri, on March 22,1982. John E. Shaw, Acting Director, Central Region. [FR Doc. 82-8592 Filed 3-81-82; 8:45 am] BILLING CODE 4910-13-M 14 CFR Part 71 [Airspace Docket No. 82-AW P-4] Designation of Federal Airways, Area Low Routes, Controlled Airspace, and Reporting Points; Designation of Temporary Control Zone, Daggett, California AGENCY: Federal Aviation Administration (FAA), DOT. a c t io n : Final rule. SUMMARY: This rule establishes a temporary control zone for the Barstow- Daggett Airport, Daggett, California. This action will provide controlled airspace for aircraft/helicopters making instrument approaches to the Barstow- Daggett Airport during the “Gallant Eagle 82” United States Readiness Command Exercise. EFFECTIVE DATE: March 22,1982. ADDRESSES: Federal Aviation Administration, Air Traffic Division, Chief, Airspace and Procedures Branch,