Rules and Regulations. Final rule

Agency: Federal Aviation Administration (FAA), DOT
Action: Final rule
Citation: FR Doc. 07-1937 · RIN 2120-AA64 · 14 CFR 39

Summary

We are adopting a new airworthiness directive (AD) that supersedes AD 72-22-01, which applies to certain Raytheon Aircraft Company (RAC) (The Beech Aircraft Company and BEECH previously held Type Certificate Nos. 3A15, 3A16, 5A3, and A-777) Models 33, 35, 36, 45, and 95 series airplanes. AD 72-22-01 currently requires you to determine if each uplock roller is of the greasible type (one having a drilled and grooved inner race), replace any nongreasible uplock roller (one having a solid inner race) with the greasible type before further flight, install hollow zerk-ended mounting bolts on the uplock rollers, and repetitively lubricate the uplock mechanism. Since we issued AD 72-22-01, there was a recent incident involving a RAC Model 95-B55B (T-42A) airplane where a seizure of the uplock rollers occurred. This malfunction of the uplock rollers is addressed in AD 72-22-01. Thus, the FAA has determined that the actions of AD 72-22-01 should also apply to certain serial numbers of the Model 95-B55B (T-42A) airplanes. Consequently, this AD retains all the actions of AD 72-22-01, adds those Model 95-B55B (T-42A) airplanes to the applicability of this AD, and lists the specific serial numbers. We are issuing this AD to decrease the possibility of gear-up landings caused by seizure of the uplock rollers.

Dates

This AD becomes effective on May 25, 2007. On May 25, 2007 the Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD.

Supplementary Information

Discussion On December 4, 2006, we issued a proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to certain RAC Models 33, 35, 36, 45, and 95 series airplanes. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on December 11, 2006 (71 FR 71494). The NPRM proposed to retain all the actions of AD 72-22-01, add those Model 95-B55B (T-42A) airplanes to the applicability of the proposed AD, and list the specific serial numbers. Comments We provided the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal and FAA's response to each comment: Comment Issue No. 1: Change Compliance Time for AD 72-22-01 Kenneth R. Pearce, Pearce Aircraft Services, Inc, writes that AD 72-22-01, which requires compliance within 300 hours time-in-service (TIS), should be changed to 100 hours TIS or the next annual inspection, whichever comes last. The 300-hour limit casts doubt on the urgent need for a flight safety action. The FAA has reviewed and considered the commenter's comments and does not agree. The purpose of the proposed AD is not to change the requirements of AD 72-22-01, but to add another model to the applicability list. Service history has shown that the 300-hour inspection is adequate to remove the unsafe condition. Therefore, the FAA will maintain the current requirements from the NPRM. We are not changing the final rule AD action based on this comment. Comment Issue No. 2: No Need for the Required Recurring 100-Hour TIS Lubrication Kenneth R. Pearce also writes that there is no need for the AD to require the recurring 100-hour TIS lubrication. He explains that maintenance of the uplock roller is thoroughly documented in the airplane maintenance manuals (AMMs), the 100-hour TIS/annual inspection checklist does list lubrication as required following the AMMs, and the Pilots Operating Handbook/FAA-approved Airplane Flight Manual directs checking the uplock roller for free rotation before flight. In addition, Pearce also notes that the landing gear system is a complex assembly that is totally dependent on exacting adjustment of several switches, adjustment of actuator rods, strength of springs, and timely lubrication of all grease fittings with appropriate lubricants. If the maintenance is proper, the rollers will not restrict the landing gear movement because they touch the uplock block only in severe turbulence. The FAA has reviewed and considered the commenter's comments and does not agree. The purpose of the proposed AD is not to change the requirements of AD 72-22-01, but to add another model to the applicability list. The commenter concurs with the proposed AD to include the model 95-B55B (T-42A) airplane. At the time of AD 72-22-01, it was necessary to address these repetitive lubrications through AD action. If a maintenance manual is revised to add procedures, that does not eliminate the need for the AD since the only way to ensure that all revised maintenance procedures are incorporated is through an AD. We have determined that the 100-hour TIS repetitive lubrication requirement is still necessary to address the unsafe condition. We are not changing the final rule AD action based on this comment. Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed except for minor editorial corrections. We have determined that these minor corrections: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Costs of Compliance We estimate that this AD affects 9,714 airplanes in the U.S. registry, including those airplanes affected by AD 72-22-01. We estimate the following costs to do the actions to determine if each uplock roller is of the greasible type (one having a drilled and grooved inner race), replace any nongreasible uplock roller (one having a solid inner race) with the greasible type before further flight, install hollow zerk-ended mounting bolts on the uplock rollers, and initially lubricate the uplock mechanism: Labor cost Parts cost Total cost per airplane Total cost on U.S. operators 2 work-hours × $80 per hour = $160 $30 $190 $1,845,660 We estimate the following costs for each lubrication of the uplock mechanism: Labor cost Parts cost Total cost per airplane Total cost on U.S. operators 1 work-hour × $80 per hour = $80 None $80 $777,120 The estimated total cost on U.S. operators includes the cumulative costs associated with those airplanes affected by AD 72-22-01 and those airplanes being added in 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 AD. 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; 2. Is not a “significant rule” under the 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 other information as included in the Regulatory Evaluation) and placed it in the AD Docket. You may get a copy of this summary by sending a request to us at the address listed under ADDRESSES . Include “Docket No. FAA-2006-26075; Directorate Identifier 2006-CE-55-AD” in your request. 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 Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (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. FAA amends § 39.13 by removing AD 72-22-01, Amendment 39-1544, and adding a new AD to read as follows: 2007-08-08 Raytheon Aircraft Company (The Beech Aircraft Company and BEECH previously held Type Certificate Nos. 3A15, 3A16, 5A3, and A-777): Amendment 39-15025; Docket No. FAA-2006-26075; Directorate Identifier 2006-CE-55-AD. Effective Date (a) This AD becomes effective on May 25, 2007. Affected ADs (b) This AD supersedes AD 72-22-01, Amendment 39-1544. Applicability (c) This AD applies to the following airplane models and serial numbers (SNs) that are certificated in any category: (1) Group 1 (maintains the actions from AD 72-22-01): Model SNs (i) 35-33, 35-A33, 35-B33, 35-C33, E33, F33, and G33 CD-1 through CD-1256. (ii) 35-C33A, E33A, and F33A CE-1 through CE-349. (iii) E33C and F33C CJ-1 through CJ-30. (iv) 35, A35, B35, C35, D35, E35, F35, G35, H35, J35, K35, M35, N35, P35, S35, V35, V35A, and V35B D-1 through D-9287. (v) 36 and A36 E1 through E-283. (vi) A45 (T-34A, B45) and D45 (T-34B) All. (vii) 95-55, 95-A55, 95-B55, and 95-B55A TC-1 through TC-1402. (viii) 95-C55, 95-C55A, D55, D55A, E55, and E55A TE-1 through TE-846. (ix) 56TC and A56TC TG-1 through TG-94. (x) 58 TH-1 through TH-174. (xi) 95, B95, B95A, D95A, and E95 TD-2 through TD-721. (2) Group 2: Model 95-B55B (T-42A) airplanes, SNs TF-1 through TF-70. Unsafe Condition (d) This AD results from a recent incident involving a Raytheon Aircraft Company (RAC) Model 95-B55B (T-42A) airplane where a seizure of the uplock rollers occurred. We are issuing this AD to decrease the possibility of gear-up landings caused by seizure of the uplock rollers. Compliance (e) To address this problem, you must do the following, unless already done: Actions Compliance Procedures (1) Determine if each uplock roller is of the greasible type (one having a drilled and grooved inner race) (i) For Group 1 airplanes: Within 300 hours time-in-service (TIS) after October 25, 1972 (the effective date of AD 72-22-01) Follow Beechcraft Service Instructions No. 0448-211, Rev. I (undated), or Beechcraft Service Instructions No. 0448-211 (undated). (ii) For Group 2 airplanes: Within 300 hours TIS after May 25, 2007 (the effective date of this AD). (2) Replace any nongreasible uplock roller (one having a solid inner race) with the greasible type (i) For Group 1 airplanes: Before further flight after the determination required by paragraph (e)(1)(i) of this AD (ii) For Group 2 airplanes: Before further flight after the determination required by paragraph (e)(1)(ii) of this AD. Follow Beechcraft Service Instructions No. 0448-211, Rev. I (undated), or Beechcraft Service Instructions No. 0448-211 (undated). (3) Install hollow zerk-ended mounting bolts on the uplock rollers (i) For Group 1 airplanes: Within 300 hours TIS after October 25, 1972 (the effective date of AD 72-22-01) (ii) For Group 2 airplanes: Within 300 hours TIS after May 25, 2007 (the effective date of this AD). Follow Beechcraft Service Instructions No. 0448-211, Rev. I (undated), or Beechcraft Service Instructions No. 0448-211 (undated). (4) Lubricate the uplock mechanism (i) For Group 1 airplanes: Initially within 300 hours TIS after October 25, 1972 (the effective date of AD 72-22-01). Repetitively lubricate thereafter at intervals not to exceed 100 hours TIS Follow Beechcraft Service Instructions No. 0448-211, Rev. I (undated), or Beechcraft Service Instructions No. 0448-211 (undated). (ii) For Group 2 airplanes: Initially within 300 hours TIS after May 25, 2007 the effective date of this AD. Repetitively lubricate thereafter at intervals not to exceed 100 hours TIS. Alternative Methods of Compliance (AMOCs) (f) The Manager, Wichita Aircraft Certification Office, FAA, ATTN: Anthony Flores, Aerospace Engineer, 1801 Airport Road, Wichita, Kansas 67209; telephone: (316) 946-4174; facsimile: (316) 946-4107, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (g) AMOCs approved for AD 72-22-01 are approved for this AD. Material Incorporated by Reference (h) You must use Beechcraft Service Instructions No. 0448-211, Rev. I (undated), or Beechcraft Service Instructions No. 0448-211 (undated), 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 Beechcraft Service Instructions No. 0448-211 (undated), and Beechcraft Service Instructions No. 0448-211, Rev. I (undated), under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-0085; telephone: (800) 429-5372 or (316) 676-3140. (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 April 6, 2007. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-7048 Filed 4-19-07; 8:45 am] BILLING CODE 4910-13-P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2007-27343; Directorate Identifier 2007-SW-05-AD; Amendment 39-15030; AD 2007-05-51] RIN 2120-AA64 Airworthiness Directives; MD Helicopters Inc. (MDHI) Model MD600N Helicopters AGENCY: Federal Aviation Administration, DOT. ACTION: Final rule; request for comments. SUMMARY: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2007-05-51, which was sent previously to all known U.S. owners and operators of MDHI Model MD600N helicopters by individual letters. This AD requires, before further flight, a visual and eddy current inspection of each lateral mixer output link assembly (mixer link) and replacing any cracked mixer link. This AD also requires performing an eddy current inspection on each mixer link before installing it on any helicopter. This amendment is prompted by the discovery of 3 cracked mixer links. The actions specified by this AD are intended to detect a crack in the mixer link, which could result in failure of the mixer link and subsequent loss of control of the helicopter. DATES: Effective May 7, 2007, to all persons except those persons to whom it was made immediately effective by Emergency AD 2007-05-51, issued on February 17, 2007, which contained the requirements of this amendment. Comments for inclusion in the Rules Docket must be received on or before June 19, 2007. ADDRESSES: Use one of the following addresses to submit comments on this AD: • DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically; • Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically; • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590; • Fax: (202) 493-2251; or • Hand Delivery: Room PL-401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. You may get the service information identified in this AD from MD Helicopters Inc., Attn: Customer Support Division, 4555 E. McDowell Rd., Mail Stop M615, Mesa, Arizona 85215-9734, telephone 1-800-388-3378, fax 480-346-6813, or on the Web at http://www.mdhelicopters.com. Examining the Docket You may examine the docket that contains the AD, any comments, and other information on the Internet at http://dms.dot.gov, or in person at the Docket Management System (DMS) Docket Offices between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647-5227) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the DMS receives them. FOR FURTHER INFORMATION CONTACT: Jon Mowery, Aviation Safety Engineer, FAA, Los Angeles Aircraft Certification Office, Airframe Branch, 3960 Paramount Blvd., Lakewood, California 90712, telephone (562) 627-5322, fax (562) 627-5210. SUPPLEMENTARY INFORMATION: On February 17, 2007 we issued Emergency AD 2007-05-51 for MDHI Model MD600N helicopters, which requires, before further flight, a visual and eddy current inspection of each mixer link and replacing any cracked mixer link. The Emergency AD also requires performing an eddy current inspection on each mixer link before installing it on any helicopter. That action was prompted by the discovery of a cracked mixer link, part number (P/N) 600N7636-1, on an in-service MDHI Model MD600N helicopter. Cracks were also found on two additional mixer links, P/N 600N7636-3, which were being held as spares. The cracks on all three mixer links run through the bearing end area of the mixer link and emanate from staking marks in the mixer link. Cracks in the mixer link, if not detected, could result in failure of the mixer link and subsequent loss of control of the helicopter. We have reviewed MDHI Service Bulletin No. SB600N-044, dated February 16, 2007 (SB), which describes procedures for a one-time visual inspection and an eddy current inspection of the mixer link. The SB includes only P/Ns 600N7636-1, and -3 in its effectivity, however, because the exact cause of the cracks is unknown, and the -9 and -11 are similar designs, we have included them in the applicability of this AD. We are also requiring an eddy current inspection of each affected mixer link before installing it on any helicopter. Since the unsafe condition described is likely to exist or develop on other MDHI Model MD600N helicopters of the same type design, we issued Emergency AD 2007-05-51 to detect a crack in the mixer link, which could result in failure of the mixer link and subsequent loss of control of the helicopter. The AD requires, before further flight, the following for each mixer link, P/N 600N7636-1, -3, -9, and -11: • Removing each mixer link, and visually inspecting, with a bright light and a 10x or higher magnifying glass, the areas on the ends of the mixer link on both sides around the bearing bore for any crack, • Performing an eddy current inspection of each mixer link in the bearing end areas, and • Replacing any cracked mixer link with an airworthy mixer link on which an eddy current inspection has been performed. The AD also requires performing an eddy current inspection on each mixer link before installing it on any helicopter. The short compliance time involved is required because the previously described critical unsafe condition can adversely affect the structural integrity and controllability of the helicopter. Therefore, the actions described previously are required before further flight, and this AD must be issued immediately. A one-time flight permit is allowed for flying the helicopter to a location where the eddy current inspection can be performed, provided that no crack is found during the visual inspection required in paragraph (a) of this AD and that the helicopter's airspeed does not exceed 100 knots. The requirements of this AD are interim actions; the manufacturer continues to investigate the cause of the cracks and, based on that investigation, we will determine either follow-on actions or a terminating action for the requirements of this AD. Since it was found that immediate corrective action was required, notice and opportunity for prior public comment thereon were impracticable and contrary to the public interest, and good cause existed to make the AD effective immediately by individual letters issued on February 17, 2007 to all known U.S. owners and operators of MDHI Model MD600N helicopters. These conditions still exist, and the AD is hereby published in the Federal Register as an amendment to 14 CFR 39.13 to make it effective to all persons. We estimate that this AD will affect 26 helicopters of U.S. registry. It will take approximately: • 2 work hours to remove, inspect, and replace both mixer links on each helicopter, • 5 work hours for an eddy current inspection of both mixer links, • $80 per work hour, and • $865 for a mixer link, if necessary. Based on these figures, we estimate the total cost impact of the AD on U.S. operators to be $18,885, assuming that a visual and eddy current inspection are performed on each mixer link installed on a helicopter and that 5 of the 52 mixer links are cracked and need to be replaced. Comments Invited This AD is a final rule that involves requirements that affect flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to submit any written data, views, or arguments regarding this AD. Send your comments to an address listed under ADDRESSES . Include “Docket No. FAA-2007-27343; Directorate Identifier 2007-SW-05-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://dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this AD. Using the search function of our docket web site, you can find and read the comments to any of our dockets, including the name of the individual who sent the comment. You may review the DOT's complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477-78), or you may visit http://dms.dot.gov . 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 the regulation: 1. Is not a “significant regulatory action” under Executive Order 12866; 2. Is not a “significant rule” under the 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 an economic evaluation of the estimated costs to comply with this AD. See the DMS to examine the economic evaluation. 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (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. Section 39.13 is amended by adding a new airworthiness directive to read as follows: 2007-05-51 MD Helicopters Inc. (MDHI): Amendment 39-15030. Docket No. FAA-2007-27343; Directorate Identifier 2007-SW-05-AD. Applicability: Model MD600N helicopters, with a lateral mixer output link assembly (mixer link), part number (P/N) 600N7636-1, -3, -9, or -11 installed, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To detect a crack in the mixer link, which could result in failure of the mixer link and subsequent loss of control of the helicopter, accomplish the following: (a) Before further flight: (1) Remove each mixer link and visually inspect, with a bright light and a 10x or higher magnifying glass, the shaded areas around the bearing bore for any crack as depicted in the following Figure 1: ER20AP07.003 (2) Perform an eddy current inspection of each mixer link in the bearing end areas. (3) Replace any cracked mixer link with an airworthy mixer link on which an eddy current inspection has been performed. Note: MDHI Service Bulletin No. SB600N-044, dated February 16, 2007, pertains to the subject of this AD. (b) Perform an eddy current inspection on each mixer link before installing it on any helicopter. (c) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Manager, Los Angeles Aircraft Certification Office, FAA, ATTN: Jon Mowery, Aviation Safety Engineer, Airframe Branch, 3960 Paramount Blvd., Lakewood, California 90712, telephone (562) 627-5322, fax (562) 627-5210, for information about previously approved alternative methods of compliance. (d) A one-time special flight permit may be issued in accordance with 14 CFR 21.197 and 21.199 to operate the helicopter to a location where the eddy current inspection requirements of this AD can be accomplished provided that no crack is found during the visual inspection required in paragraph (a) of this AD and that the helicopter's airspeed does not exceed 100 knots. (e) This amendment becomes effective on May 7, 2007, to all persons except those persons to whom it was made immediately effective by Emergency AD 2007-05-51, issued February 17, 2007, which contained the requirements of this amendment. Issued in Fort Worth, Texas, on April 5, 2007. Mark R. Schilling, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E7-7438 Filed 4-19-07; 8:45 am] BILLING CODE 4910-13-P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2007-27786; Directorate Identifier 2007-CE-031-AD; Amendment 39-15031; AD 2007-09-01] RIN 2120-AA64 Airworthiness Directives; Cessna Aircraft Company Models 182H, 182J, 182K, 182L, 182M, 182N, 182P, 182Q, and 182R 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) Model 182 series airplanes that are equipped with Air Plains Services Corporation Supplemental Type Certificate (STC) SA00152WI. This AD requires you to disconnect or remove the electrical cable between the forward ground power relay and the starter relay, install a placard, inspect the fuel line between the auxiliary electric fuel pump and the engine-driven fuel pump for chafing, and replace the fuel line if chafing is found. This AD results from a report of an in-flight and post-landing engine compartment fire. We are issuing this AD to detect and correct interference between the ground power electrical cable, the fuel strainer cable, and the fuel line between the auxiliary electric fuel pump and the engine-driven fuel pump. This condition could lead to a fire in the engine compartment. DATES: This AD becomes effective on April 25, 2007. On April 25, 2007 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 June 19, 2007. ADDRESSES: Use one of the following addresses to comment on this AD. • DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-0001. • Fax: (202) 493-2251. • Hand Delivery: Room PL-401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Federal eRulemaking Portal: Go to http://www.regulations.gov . Follow the instructions for submitting comments. To get the service information identified in this AD, contact Air Plains Services Corporation, P.O. Box 541, Wellington, KS 67152; phone: 620-326-8904; Internet: http://www.airplains.com. To view the comments to this AD, go to http://dms.dot.gov. The docket number is FAA-2007-27786; Directorate Identifier 2007-CE-031-AD. FOR FURTHER INFORMATION CONTACT: Trenton Shepherd, Aerospace Engineer, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-4143; fax: (316) 946-4107. SUPPLEMENTARY INFORMATION: Discussion We received a report of a Cessna Model 182Q airplane with Air Plains Services Corporation STC SA00152WI installed that had an in-flight and post-landing fire. The preliminary finding, per the National Transportation Safety Board (NTSB), is that the electrical cable between the forward ground power relay and the starter relay chafed on either the fuel strainer control or on the fuel line between the auxiliary electric fuel pump and the engine-driven fuel pump. The cable shorted, welded the fuel strainer control cable to the firewall, and burned the fuel line between the auxiliary electric fuel pump and the engine-driven fuel pump. This condition, if not corrected, could result in a fuel leak and fire in the engine compartment. Relevant Service Information We reviewed Air Plains Services Corporation Mandatory Service Bulletin APS-07-01-01, dated March 5, 2007. The service information describes procedures for the following actions: • Disconnecting or removing the electrical cable between the forward ground power relay and the starter relay; • Repositioning the fuel strainer cable; • Inspecting the fuel line between the auxiliary electric fuel pump and the engine-driven fuel pump for chafing; and • Adjusting the position of the fuel line fitting at the engine-driven fuel pump. 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 you to disconnect or remove the ground power electrical cable between the forward ground power relay and the starter relay, install a placard, inspect the fuel line between the auxiliary electric fuel pump and the engine-driven fuel pump for chafing, and replace the fuel line if chafing is found. This AD is considered interim action. The FAA is working with the STC holder on developing a design change for the ground power electrical cable. If a modification is developed, the FAA will evaluate it and determine whether future rulemaking action is necessary to address this condition. In preparing this rule, we contacted type clubs and aircraft operators to get technical information and information on operational and economic impacts. We did not receive any information through these contacts. If received, we would have included a discussion of any information that may have influenced this action in the rulemaking docket. 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-2007-27786; Directorate Identifier 2007-CE-031-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://dms.dot.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. 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://dms.dot.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) 647-5227) 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 the following new airworthiness directive (AD): 2007-09-01 Cessna Aircraft Company: Amendment 39-15031; Docket No. FAA-2007-27786; Directorate Identifier 2007-CE-031-AD. Effective Date (a) This AD becomes effective on April 25, 2007. Affected ADs (b) None. Applicability (c) This AD applies to Models 182H, 182J, 182K, 182L, 182M, 182N, 182P, 182Q, and 182R airplanes, all serial numbers, that: (i) Have Air Plains Services Corporation Supplemental Type Certificate (STC) SA00152WI installed; (ii) Have a ground power receptacle mounted on the firewall (forward ground power receptacle); and (iii) Are certificated in any category. Unsafe Condition (d) This AD results from a report of an in-flight and post-landing engine compartment fire. We are issuing this AD to detect and correct interference between the ground power electrical cable, the fuel strainer cable, and the fuel line between the auxiliary electric fuel pump and the engine-driven fuel pump. This condition could lead to a fire in the engine compartment. Compliance (e) To address this problem, you must do the following, unless already done: Actions Compliance Procedures (1) Remove power to the ground power electrical cable by: Within 15 days after April 25, 2007 (the effective date of this AD) Follow Air Plains Services Corporation Mandatory Service Bulletin APS-07-01-01, dated March 5, 2007. (i) Disconnecting the electrical cable at the forward ground power relay and the starter relay, or (ii) Removing the electrical cable between the forward ground power relay and the starter relay. (2) Fabricate and install a placard as close as possible to the forward ground power receptacle that incorporates the following words (using at least 1/8-inch red letters on a white background and a red border): “GROUND POWER RECEPTACLE IS INOPERATIVE.” Before further flight after power to the ground power cable is removed per paragraph (e)(1) of this AD The owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7) may fabricate and install the placard. Make an entry into the aircraft records showing compliance with these portions of the AD in accordance with section 43.9 of the Federal Aviation Regulations (14 CFR 43.9). (3) Reposition the fuel strainer cable Within 15 days after April 25, 2007 (the effective date of this AD) Follow Air Plains Services Corporation Mandatory Service Bulletin APS-07-01-01, dated March 5, 2007. (4) Visually inspect the fuel line from the auxiliary electric fuel pump to the engine-driven fuel pump for chafing Within 15 days after April 25, 2007 (the effective date of this AD) Follow Air Plains Services Corporation Mandatory Service Bulletin APS-07-01-01, dated March 5, 2007. (5) If chafing at or beyond the limits defined in the Air Plains Services Corporation Mandatory Service Bulletin APS-07-01-01, dated March 5, 2007, is found in the inspection required by paragraph (e)(4) of this AD, replace the fuel line between the auxiliary electric fuel pump and the engine-driven fuel pump with a new hose part number AE3663161G0190 (or FAA-approved equivalent) and remove the ground power electrical cable per (e)(1)(ii) of this AD Before further flight after any inspection where evidence of chafing is found Follow Air Plains Services Corporation Mandatory Service Bulletin APS-07-01-01, dated March 5, 2007. (6) Adjust the position of the fuel line fitting at the engine-driven fuel pump Within 15 days after April 25, 2007 (the effective date of this AD) Follow Air Plains Services Corporation Mandatory Service Bulletin APS-07-01-01, dated March 5, 2007. Alternative Methods of Compliance (AMOCs) (f) The Manager, Wichita Aircraft Certification Office (ACO), FAA, ATTN: Trenton Shepherd, Aerospace Engineer, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-4143; fax: (316) 946-4107, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. 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. Material Incorporated by Reference (g) You must use Air Plains Services Corporation Mandatory Service Bulletin APS-07-01-01, dated March 5, 2007, 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 Air Plains Services Corporation, P.O. Box 541, Wellington, KS 67152; phone: 620-326-8904; Internet: http://www.airplains.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 April 13, 2007. Charles L. Smalley, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-7519 Filed 4-19-07; 8:45 am] BILLING CODE 4910-13-P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Parts 121, 135 [Docket No.: FAA-2007-26969; Amendment Nos. 121-331 and 135-109] RIN 2120-AI99 Change in Extinguishing Agent Container Requirements AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Direct final rule; request for comments. SUMMARY: This action aligns the operational and certification safety requirements regarding over-pressurization of airplane extinguishing agent containers or fire bottles to prevent bursting; and it removes an obsolete section reference from part 135. This action eliminates the requirement for an over-pressurized fire bottle to discharge extinguishing agent outside an airplane to prevent bursting, because newer non-corrosive extinguishing agents can now be discharged inside an airplane without degrading an airframe. DATES: Effective June 4, 2007. Comments for inclusion in the Rules Docket must be received on or before May 21, 2007. ADDRESSES: Commenting on this Direct Final Rule. You may send comments identified by Docket Number FAA-2007-26969, using any of the following methods: • DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-0001. • Fax: 1-202-493-2251. • Hand Delivery: Room PL-401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. FOR FURTHER INFORMATION CONTACT: Joel Schlossberg, Aircraft Maintenance Division, Flight Standards Service, Federal Aviation Administration, 800 Independence Avenue, SW., Washington, DC 20591. Telephone: (202-267-8908); facsimile: (202-267-5115); e-mail: joel.schlossberg@faa.gov. SUPPLEMENTARY INFORMATION: Later in this preamble under the Additional Information section, we discuss how you can comment on this direct final rule and how we will handle your comments. Included in this discussion is related information about the docket. We also discuss how you can get a copy of this direct final rule and any related rulemaking documents. Authority for This Rulemaking The FAA's authority to issue rules regarding aviation safety is found in Title 49 of the United States Code. This rulemaking is promulgated under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, “General requirements.” Under that section, the FAA is charged with promoting safe flight of civil aircraft in air commerce by prescribing: • Minimum standards required in the interest of safety for the design and performance of aircraft; and • Regulations for other practices, methods, and procedures the Administrator finds necessary for safety in air commerce and national security. This regulation is within the scope of that authority because it prescribes: • Standards for the safe operation of transport category airplanes; and • Practices, methods, and procedures that the Administrator finds necessary for safety in air commerce and national security. Background Since at least 1949, the FAA has required fire extinguishing containers (fire bottle) to have a pressure relief line to prevent a container from bursting in case of excessive internal pressure. This pressure relief line would discharge the extinguishing agent from the fire bottle. Historically, fire extinguishing agents were corrosive materials that could degrade an airframe. Therefore, in both airplane certification and operational rules, the FAA required any discharge for pressure relief to be only outside the airplane. Eventually, industry developed non-corrosive extinguishing agents. Therefore, on March 17, 1977, the FAA published in the Federal Register a final rule 1 that amended the airplane certification rules in 14 CFR 25.1199 to adopt a performance standard. This rule changed the airplane certification standards, to require airplane manufacturers to place pressure relief discharge lines in such a way to not damage an airplane. See 40 FR 21866, 21871. Thus, the pressure relief discharge line could be located either inside or outside the airplane, as long as a discharge would not damage the airplane. 1 Airworthiness Review Program—Amendment No. 4: Powerplant Amendments (42 FR 15034). However, the corresponding operational requirements in § 121.267, and by reference in § 135.169, were not changed in 1977 and therefore only allow for the termination of the fire bottle discharge line outside the airplane. As a result of this discrepancy, in a request dated July 5, 2006, Aeronautical Charters, Inc. submitted a petition for exemption 2 from § 121.267 for their part 135 airplane model (Citation 550). The difference between the certification and operational requirements has caused confusion, which is likely to result in more exemption requests. The FAA proceeds with this direct final rule to align the certification and operational requirements. This rule maintains safety because the reason for the original limitation (outside discharge) is no longer a concern with the development and use of non-corrosive extinguishing agents. 2 Docket FAA-2006-25325. This direct final rule also removes an obsolete section reference from part 135. In a December 20, 1995 rulemaking, 3 the FAA removed and reserved § 121.213, which contained special airworthiness requirements. We included those requirements in § 121.211 (Applicability). However, we inadvertently left a reference to § 121.213 in § 135.169(a). This direct final rule amends part 135 to remove the reference to § 121.213. 3 Commuter Operations and General Certification and Operations Requirements; Air Carrier and Commercial Operator Training Programs; Final Rules (60 FR 65832). The Direct Final Rule Process The FAA anticipates that this regulation will not result in adverse or negative comment and, therefore, we are issuing it as a direct final rule. We believe we will not get adverse comments because this action will— • Correct a discrepancy in the certification and operational rules that could potentially ground affected airplanes. • Eliminate the need for operators to petition the FAA for an exemption from the fire bottle requirements in § 121.267. • Not place any new requirements or additional burden on affected operators. Unless we receive a written adverse or negative comment, or a written notice of intent to submit an adverse or negative comment within the comment period, the regulation will become effective on the date specified above. After the close of the comment period, the FAA will publish a document in the Federal Register that indicates we received no adverse or negative comments and confirms the date the final rule will become effective. If the FAA does receive, within the comment period, an adverse or negative comment, or written notice of intent to submit such a comment, we will publish a document withdrawing the direct final rule in the Federal Register , and a notice of proposed rulemaking may be published with a new comment period. Paperwork Reduction Act There are no current or new requirements for information collection associated with these amendments. International Compatibility The FAA has reviewed corresponding International Civil Aviation Organization International Standards and Recommended practices and similar regulations of foreign authorities, where they exist, and has identified no differences in these proposed amendments and the foreign regulations. Economic Evaluation, Regulatory Flexibility Act, Trade Impact Assessment, and Unfunded Mandates Assessment Changes to Federal regulations must undergo several economic analyses. First, Executive Order 12866 directs that each Federal agency shall propose or adopt a regulation only upon a reasoned determination that the benefits of the intended regulation justify its costs. Second, the Regulatory Flexibility Act of 1980 (Pub. L. 96-354) requires agencies to analyze the economic impact of regulatory changes on small entities. Third, the Trade Agreements Act (Pub. L. 96-39) prohibits agencies from setting standards that create unnecessary obstacles to the foreign commerce of the United States. In developing U.S. standards, the Trade Act requires agencies to consider international standards and, where appropriate, that they be the basis of U.S. standards. Fourth, the Unfunded Mandates Reform Act of 1995 (Pub. L. 104-4) requires agencies to prepare a written assessment of the costs, benefits, and other effects of proposed or final rules that include a Federal mandate likely to result in the expenditure by State, local, or tribal governments, in the aggregate, or by the private sector, of $100 million or more annually (adjusted for inflation with base year of 1995). This portion of the preamble summarizes the FAA's analysis of the economic impacts of this final rule. Department of Transportation Order DOT 2100.5 prescribes policies and procedures for simplification, analysis, and review of regulations. If the expected cost impact is so minimal that a proposed or final rule does not warrant a full evaluation, this order permits a statement to that effect and the basis for it to be included in the preamble if a full regulatory evaluation of the cost and benefits is not prepared. Such a determination has been made for this final rule. The reasoning for this determination follows: This action aligns the operational and certification safety requirements regarding over-pressurization of airplane extinguishing agent containers or fire bottles to prevent bursting; and it removes an obsolete section reference from part 135. This action eliminates the requirement for an over-pressurized fire bottle to discharge extinguishing agent outside an airplane to prevent bursting, because newer non-corrosive extinguishing agents can now be discharged inside an airplane without degrading an airframe. Regulatory Flexibility Determination The Regulatory Flexibility Act of 1980 (Pub. L. 96-354) (RFA) establishes “as a principle of regulatory issuance that agencies shall endeavor, consistent with the objectives of the rule and of applicable statutes, to fit regulatory and informational requirements to the scale of the businesses, organizations, and governmental jurisdictions subject to regulation. To achieve this principle, agencies are required to solicit and consider flexible regulatory proposals and to explain the rationale for their actions to assure that such proposals are given serious consideration.” The RFA covers a wide-range of small entities, including small businesses, not-for-profit organizations, and small governmental jurisdictions. Agencies must perform a review to determine whether a rule will have a significant economic impact on a substantial number of small entities. If the agency determines that it will, the agency must prepare a regulatory flexibility analysis as described in the RFA. However, if an agency determines that a rule is not expected to have a significant economic impact on a substantial number of small entities, section 605(b) of the RFA provides that the head of the agency may so certify and a regulatory flexibility analysis is not required. The certification must include a statement providing the factual basis for this determination, and the reasoning should be clear. This final rule aligns the operational and certification safety requirements regarding over-pressurization of airplane extinguishing agent containers or fire bottles to prevent bursting; and it removes an obsolete section reference from part 135. Its economic impact is minimal. Therefore, as the FAA Administrator, I certify that this rule will not have a significant economic impact on a substantial number of small entities. Trade Impact Assessment The Trade Agreements Act of 1979 prohibits Federal agencies from engaging in any standards or related activities that create unnecessary obstacles to the foreign commerce of the United States. Legitimate domestic objectives, such as safety, are not considered unnecessary obstacles. The statute also requires consideration of international standards and where appropriate, that they be the basis for U.S. standards. The FAA has assessed the potential effect of this final rule and has determined that it will have the same cost relieving impact on domestic and international entities and thus has a neutral trade impact. Unfunded Mandates Assessment Title II of the Unfunded Mandates Reform Act of 1995 (Pub. L. 104-4) requires each Federal agency to prepare a written statement assessing the effects of any Federal mandate in a proposed or final agency rule that may result in a $100 million or more expenditure (adjusted annually for inflation). The FAA currently uses an inflation-adjusted value of $128.1 million in lieu of $100 million. This final rule does not contain such a mandate. Therefore, the requirements of Title II do not apply to this regulation. Executive Order 13132, Federalism The FAA has analyzed this final rule under the principles and criteria of Executive Order 13132, Federalism. We determined that this action will not have a substantial direct effect on the States, or the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, we determined that this final rule does not have federalism implications. Environmental Analysis FAA Order 1050.1E identifies FAA actions that are categorically excluded from preparation of an environmental assessment or environmental impact statement under the National Environmental Policy Act in the absence of extraordinary circumstances. The FAA has determined this proposed rulemaking action qualifies for the categorical exclusion identified in paragraph 312 and involves no extraordinary circumstances. Regulations that Significantly Affect Energy Supply, Distribution, or Use The FAA has analyzed this final rule under Executive Order 13211, Actions Concerning Regulations that Significantly Affect Energy Supply, Distribution, or Use (66 FR 28355, May 18, 2001). We have determined that it is not a “significant energy action” under the executive order because it is not a “significant regulatory action” under Executive Order 12866, and it is not likely to have a significant adverse effect on the supply, distribution, or use of energy. Additional Information Commenting on this Direct Final Rule You may send comments identified by Docket Number FAA-2007-26969, using any of the following methods: • DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-0001. • Fax: 1-202-493-2251. • Hand Delivery: Room PL-401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Availability of Rulemaking Documents You can get an electronic copy using the Internet by: 1. Searching the Department of Transportation's electronic Docket Management System (DMS) web page ( http://dms.dot.gov/search ); 2. Visiting the FAA's Regulations and Policies web page at http://www.faa.gov/regulations_policies/; or 3. Accessing the Government Printing Office's web page at http://www.gpoaccess.gov/fr/index.html. You can also get a copy by sending a request to the Federal Aviation Administration, Office of Rulemaking, ARM-1, 800 Independence Avenue, SW., Washington, DC 20591, or by calling (202) 267-9680. Make sure to identify the docket number, notice number, or amendment number of this rulemaking. Small Business Regulatory Enforcement Fairness Act The Small Business Regulatory Enforcement Fairness Act (SBREFA) of 1996 requires FAA to comply with small entity requests for information or advice about compliance with statutes and regulations within its jurisdiction. If you are a small entity and you have a question regarding this document, you may contact your local FAA official, or the person listed under the FOR FURTHER INFORMATION CONTACT heading at the beginning of the preamble. You can find out more about SBREFA on the Internet at http://www.faa.gov/regulations_policies/rulemaking/sbre_act/. List of Subjects 14 CFR Part 121 Air carriers, Aircraft, Airmen, Alcohol abuse, Aviation safety, Reporting and recordkeeping requirements, Safety, Transportation. 14 CFR Part 135 Aircraft, Airmen, Aviation safety, Reporting and recordkeeping requirements. The Amendment In consideration of the foregoing, the Federal Aviation Administration amends Chapter I of Title 14, Code of Federal Regulations as follows: PART 121—OPERATING REQUIREMENTS: DOMESTIC, FLAG, AND SUPPLEMENTAL OPERATIONS 1.The authority citation for part 121 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 40119, 41706, 44101, 44701-44702, 44705, 44709-44711, 44713, 44716-44717, 44722, 44901, 44903-44904, 44912, 45101-45105, 46105, 46301. 2. Section 121.267 is revised to read as follows: § 121.267 Extinguishing agent container pressure relief mechanism. (a) Extinguishing agent containers must be provided with a pressure relief mechanism to prevent bursting of the container because of excessive internal pressures. The discharge line from the relief connection must be installed in a manner so it can be inspected from the ground. Depending upon whether the discharge line terminates outside or inside the airplane, the certificate holder must accomplish the following inspections pre-departure: (1) The discharge line terminates outside the airplane. As part of the pre-departure check, visually inspect the pressure indicator at the end of the discharge line to confirm that the container has not discharged. (2) The discharge line terminates inside the airplane. As part of a pre-departure check, visually inspect the pressure indicator for the container for loss of pressure within the container. (b) The certificate holder also must ensure that only non-corrosive extinguishing agents are used in systems where the pressure discharge line terminates inside the airplane. PART 135—OPERATING REQUIREMENTS: COMMUTER AND ON DEMAND OPERATIONS AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT 3. The authority citation for part 135 continues to read as follows: Authority: 49 U.S.C. 106(g), 41706, 44113, 44101, 44701-44702, 44705, 44709, 44711-44713, 44715-44717, 44722. 4. Amend § 135.169 by revising paragraph (a) to read as follows: § 135.169 Additional airworthiness requirements. (a) Except for commuter category airplanes, no person may operate a large airplane unless it meets the additional airworthiness requirements of §§ 121.215 through 121.283 and 121.307 of this chapter. Marion C. Blakey, Administrator. [FR Doc. 07-1937 Filed 4-19-07; 8:45 am]