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(e) Reason

This AD was prompted by the discovery of a number of incorrectly calibrated angle of attack (AOA) transducers installed in the stall protection system. We are issuing this AD to detect and replace incorrectly calibrated AOA transducers; incorrect calibration of the transducers could result in late activation of the stick pusher.
(f) Compliance

Comply with this AD within the compliance times specified, unless already done.
(g) Retained Replacement of AOA Transducers With No Changes

This paragraph restates the requirements paragraph (g) of AD 2016–08–05, with no changes. Within 2,500 flight hours or 12 months, whichever occurs first after May 18, 2016 (the effective date of AD 2016–08–05), replace the AOA transducers identified in paragraph 1.A., ‘‘Effectivity,’’ of Bombardier Service Bulletin 670BA–27–069, dated March 30, 2015, with correctly calibrated AOA transducers, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 670BA–27–069, dated March
30, 2015.

(h) Retained Parts Installation Prohibition, With a Change to the Affected Parts Language

This paragraph restates the parts installation prohibition specified in paragraph (h) of AD 2016–08–05, with a change to the affected parts language. As of May 18, 2016 (the effective date of AD 2016– 08–05), no person may install, on any airplane, an AOA transducer having a part number and serial number listed in paragraph 1.A., ‘‘Effectivity,’’ of Bombardier Service Bulletin 670BA–27–069, dated March
30, 2015.

(i) Other FAA AD Provisions

The following provisions also apply to this
AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office (ACO), ANE–170, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the ACO, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone: 516–228–7300; fax: 516–794– 5531. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD.

(2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, New York ACO, ANE–170, FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.’s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature.

(j) Related Information

Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian AD CF–2015–18, dated July 16, 2015, for related information. This MCAI may be
found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2016–7265.

(k) Material Incorporated by Reference

(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise.

(3) The following service information was approved for IBR on May 18, 2016, (81 FR 21709, April 13, 2016).

(i) Bombardier Service Bulletin 670BA–27– 069, dated March 30, 2015.

(ii) Reserved. (4) For service information identified in this AD, contact Bombardier, Inc., 400 Co ˆ teVertu Road West, Dorval, Que  ́bec H4S 1Y9, Canada; Widebody Customer Response Center North America toll-free telephone: 1– 866–538–1247 or direct-dial telephone: 1– 514–855–2999; fax: 514–855–7401; email: ac.yul@aero.bombardier.com; Internet: http://www.bombardier.com.

(5) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221.

(6) You may view this service information that is incorporated by reference 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/cfr/ibr-locations.html.

Issued in Renton, Washington, on June 13,

2016. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2016–14579 Filed 6–21–16; 8:45 am]

**BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–0105; Directorate Identifier 2008–SW–58–AD; Amendment 39–**  **18562; AD 2016–12–13]**

**RIN 2120–AA64**

**Airworthiness Directives; Airbus Helicopters (Previously Eurocopter**  **France) Helicopters**

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Final rule.

**SUMMARY :**  We are superseding Airworthiness Directive (AD) 2000–05– 17 and AD 2001–04–12, which apply to Eurocopter France (now Airbus Helicopters) Model EC120B helicopters. AD 2000–05–17 and AD 2001–04–12 required repetitive visual checks of the engine-to-main gearbox (MGB) coupling tube assembly (coupling tube) for a crack and replacing any cracked tube with an airworthy tube. This new AD requires removing certain engine mount parts from service, measuring the height of the engine mounting base for certain helicopters, replacing the engine mount if a certain height is exceeded, inspecting the flared coupling on certain helicopters for a crack, and replacing the coupling if it is cracked. Since we issued AD 2000–05–17 and AD 2001– 04–12, there have been reports of additional cracks in coupling tubes. These actions are intended to prevent coupling tube failure, loss of engine drive, and a subsequent forced landing of the helicopter.

**DATES :**  This AD is effective July 27,

2016.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of July 27, 2016.

**ADDRESSES :**  For service information identified in this final rule, contact Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232– 0323; fax (972) 641–3775; or at http:// www.airbushelicopters.com/techpub. You may view this referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014–

0105.


### 40493 Federal Register / Vol. 81, No. 120 / Wednesday, June 22, 2016 / Rules and Regulations

Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov in Docket No. FAA–2014–0105; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the Direction Generale de L’Aviation Civile (DGAC) AD, any incorporated-by-reference information, the economic evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington,
DC 20590.

**FOR FURTHER INFORMATION CONTACT :**  James Blyn, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110; email james.blyn@faa.gov.

**SUPPLEMENTARY INFORMATION :** 

Discussion

On May 29, 2015, we issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to remove AD 2000–05–17 (65 FR 13875, March 15, 2000) and AD 2001–04–12 (66 FR 13232, March 5, 2001) and add a new AD. AD 2000–05–17 applied to Model EC120B helicopters with engine coupling tube part number (P/N) C631A1002101 and required recurring inspections of each coupling tube for a crack and replacing any cracked coupling tube with a reinforced coupling tube P/N C631A1101101. AD 2001–04–12 applied to Model EC120B helicopters with engine coupling tube P/N C631A1101101 and required repetitive visual checks of each coupling tube for a crack. AD 2000–05– 17 and AD 2001–04–12 were prompted by reports of cracks on the reinforced coupling tube and were intended to prevent coupling tube failure, loss of engine drive, and a subsequent forced landing.

The NPRM published in the Federal Register on June 16, 2015 (80 FR 34335). The NPRM was prompted by reports of additional cracks in coupling tubes. Eurocopter France (now Airbus Helicopters) determined that the washer-type engine mount may, in certain cases, induce excessive loading on the coupling tube, which results in binding that increases component wear of the inner diameter of the mounting base. Because of this, the DGAC, on behalf of the European Aviation Safety Agency (EASA), issued AD No. F–2003– 325 R1, dated May 12, 2004, for Model EC120B helicopters with engine coupling tube, P/N C631A1101101, and with an engine mount containing certain parts listed in Eurocopter Alert Service Bulletin (ASB) No. 04A005, dated July 16, 2003. DGAC AD No. F– 2003–325 R1 requires inspections for helicopters with an engine mount block modified in accordance with Eurocopter Service Bulletin (SB) No. 71–003, Revision 1, dated July 18, 2002; replacing any coupling tube that has a crack; and increasing the life limit of the coupling tube from 1,000 flight hours to 20,000 flight hours. Also, DGAC AD No. F–2003–325 R1 requires, for helicopters with a new spring-loaded engine suspension modification in accordance with Eurocopter SB No. 71–005, Revision 0, dated May 14, 2004, increasing the life limit of the coupling tube to 20,000 flight hours and canceling the repetitive inspections of the coupling tube.

The NPRM proposed to require, for helicopters with certain engine mounts, before further flight, removing from service certain engine mount parts and measuring the height of the engine mounting base. If the height is more than 10.5 millimeters, the NPRM proposed replacing the engine mount with an engine mount that does not have the affected parts. For certain other helicopters, the NPRM proposed to require within 25 hours time-in-serice (TIS) replacing the spring-type engine suspension system, dye-penetrant inspecting the flared coupling for a crack, and replacing any cracked flared coupling. The NPRM also proposed removing coupling tube P/N C631A1002101 from service and prohibiting installation of that coupling tube on any helicopter.

Since the NPRM was issued, the FAA Southwest Regional Office has relocated and a group email address has been established for requesting an FAA alternative method of compliance for a helicopter of foreign design. We have revised the contact information throughout this final rule to reflect the new address and new email address.

Comments

After our NPRM (80 FR 34335, June 16, 2015) was published, we received comments from one commenter.
Request

Airbus Helicopters disagrees with the proposed requirement to replace the spring-type engine suspension system in accordance with Eurocopter SB No. 71– 005 for helicopters with an improved engine mount under Eurocopter SB No. 71–003. Airbus Helicopters states there have been no coupling tube failures since incorporation of Eurocopter SB No. 71–003, and therefore the proposed requirement would not increase safety levels.

We disagree. Installing the improved engine mount specified in Eurocopter SB No. 71–003 extends the compliance time for a recurring visual inspection of the coupling tube from 5 hours TIS to 25 hours TIS. When issued, that recurring inspection was considered a short-term interim action until an effective modification or action was developed, approved, and available. Eurocopter SB No. 71–005 contained such an effective action to cancel that interim action and was developed and approved in May 2004.

Airbus Helicopters requested that, if we mandate the proposed requirement to replace the spring-type engine suspension system in accordance with Eurocopter SB No. 71–005, we change the proposed compliance time from 25 hours TIS to 18 months to allow for availability of parts.

We disagree. Eurocopter SB No. 71– 005 was approved May 13, 2004. The NPRM was published June 16, 2015. The substantial amount of time that has passed since the approval of the service information and publication of our NPRM provided operators with enough notice of our proposal to mandate that procedure such that availability of parts should not be an issue.

FAA’s Determination

This helicopter has been approved by the aviation authority of France and is approved for operation in the United States. Pursuant to our bilateral agreement with France, the DGAC on behalf of EASA, has kept the FAA informed of the situation described above. We are issuing this AD because we evaluated all information provided by the DGAC, reviewed the relevant information, considered the comments received, and determined the unsafe condition exists and is likely to exist or develop on other helicopters of this same type design and that air safety and the public interest require adopting the AD requirements as proposed.

Related Service Information Under 1
CFR Part 51

Eurocopter issued ASB No. 04A005, Revision 0, dated July 16, 2003, which prohibits, after June 30, 2004, operating an engine mount made up of the following parts: Support arm, P/N C714A1107201; swaged support arm, P/ N C714A1106201; left-hand supportbracket, P/N C714A1101102; and rightVerDate Sep<11>2014 16:06 Jun 21, 2016 Jkt 238001 PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 E:\FR\FM\22JNR1.SGM 22JNR1sradovich on DSK3TPTVN1PROD with RULES

### 40494 Federal Register / Vol. 81, No. 120 / Wednesday, June 22, 2016 / Rules and Regulations

hand support bracket, P/N C714A1101103. ASB No. 04A005 also specifies measuring the height of the engine mounting base and, if the height is more than 10.5 millimeters, replacing the engine mount with an engine mount that does not have the specified P/N. ASB No. 04A005 does not apply to helicopters modified with an improved engine mount in accordance with SB No. 71–003. ASB No. 04A005 also does not apply to helicopters with a serial number 1170 or larger, as the specified engine mounts are not installed on those helicopters.

Eurocopter also issued SB No. 71– 005, Revision 0, dated May 14, 2004, which contains procedures to modify the spring-type engine suspension system and dye-penetrant inspect the flared coupling assembly.

This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the **ADDRESSES** section.

Other Related Service Information

Eurocopter issued SB No. 71–003, Revision 1, dated July 18, 2002, which contains procedures to improve the engine mount. Eurocopter also issued ASB No. 05A003, Revision 2, dated July 16, 2003, for helicopters that have not been modified with an improved engine mount in accordance with SB No. 71– 003, which specifies inspecting the coupling tube for a crack every 5 hours and establishing a coupling tube life limit of 1,000 hours. For helicopters that have been modified with an improved engine mount, ASB No. 05A003 specifies inspecting the coupling tube for a crack every 25 hours and increasing the coupling tube life limit to 20,000 hours. ASB No. 05A003 was revised to Revision 3, dated May 11, 2004, to specify an optional spring-type engine suspension modification and cancel the repetitive inspection for this modified configuration.

Differences Between This AD and the
DGAC AD

This AD requires the installation of the spring-type engine suspension modification specified in Eurocopter SB No. 71–005 and does not require the repetitive inspection of the coupling tube and the engine mount base. This AD also does not require you to contact the manufacturer.
Costs of Compliance

We estimate that this AD will affect 23 helicopters of the 115 helicopters of U.S. Registry. At an average labor rate of $85 per work-hour, we estimate that operators may incur the following costs in order to comply with this AD.

Installing new mounting arms and brackets requires about 12 work-hours and required parts cost $9,194, for a total cost per helicopter of $10,214 and $234,922 for the U.S. fleet. Installing the mounting spring kit requires about 14 work-hours and required parts cost $14,621, for a total cost per helicopter of $15,811 and $363,653 for the U.S. fleet. Dye-penetrant inspecting thecoupling tube requires about 1 workhour for a cost per helicopter of $85 and $1,955 for the U.S. fleet.
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,

(2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979),

(3) Will not affect intrastate aviation in Alaska to the extent that a regulatory, and

(4) 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. 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:

■ a. Removing Airworthiness Directive (AD) 2000–05–17, Amendment 39– 11627 (65 FR 13875, March 15, 2000); and AD 2001–04–12, Amendment 39– 12131 (66 FR 13232, March 5, 2001); and

■ b. Adding the following new AD:
2016–12–13 Airbus Helicopters (Previously Eurocopter France): Amendment 39– 18562; Docket No. FAA–2014–0105; Directorate Identifier 2008–SW–58–AD.
(a) Applicability

This AD applies to Model EC120B helicopters with an engine-to-main gearbox coupling tube assembly (coupling tube), part number (P/N) C631A1101101 or P/N C631A1002101, installed, certificated in any category.

(b) Unsafe Condition

This AD defines the unsafe condition as a crack in a coupling tube. This condition could result in coupling tube failure, loss of engine drive, and a subsequent forced landing of the helicopter.

(c) Affected ADs

This AD supersedes AD 2000–05–17, Amendment 39–11627 (65 FR 13875, March 15, 2000) and AD 2001–04–12, Amendment 39–12131 (66 FR 13232, March 5, 2001).

(d) Effective Date

This AD becomes effective July 27, 2016.
(e) Compliance

You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time.
(f) Required Actions

(1) For helicopters with a serial number up to and including 1169, not modified with an improvement of the engine mount in accordance with Eurocopter Service Bulletin (SB) No. 71–003, Revision 1, dated July 18, 2002 (SB 71–003), or not modified by installing a spring-type engine suspension system in accordance with Eurocopter SB No. 71–005, Revision 0, dated May 14, 2004 (SB 71–005), before further flight:


### 40495 Federal Register / Vol. 81, No. 120 / Wednesday, June 22, 2016 / Rules and Regulations

(i) Remove from service the following engine mount parts:

(A) Support arm, P/N C714A1107201; (B) Swaged support arm, P/N C714A1106201;

(C) Left-hand support bracket, P/N C714A1101102; and

(D) Right-hand support bracket, P/N
C714A1101103.

(ii) Measure the height of the engine mounting base as depicted in Figure 1 of Eurocopter Alert SB No. 04A005, Revision 0, dated July 16, 2003. If the height is more than 10.5 millimeters, replace the engine mount with an engine mount that does not have the parts identified in paragraph (f)(1)(i) of this
AD.

(2) For helicopters with a serial number 1170 and larger or helicopters modified with an improvement of the engine mount in accordance with SB 71–003:

(i) Within 25 hours TIS, replace the springtype engine suspension system and perform a dye-penetrant inspection of the flared coupling for a crack by following the Accomplishment Instructions, paragraphs 2.B.2.a through 2.B.2.c of SB 71–005.

(ii) If there is a crack in the flared coupling, before further flight, replace the coupling with an airworthy coupling.

(3) For helicopters with coupling tube, P/ N C631A1002101, installed, before further flight, remove coupling tube, P/N C631A1002101, from service. Do not install coupling tube, P/N C631A1002101, on any helicopter.
(g) Special Flight Permits

Special flight permits may be issued provided there are no cracks in the coupling tube attachment fitting.
(h) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: James Blyn, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110; email 9- ASW-FTW-AMOC-Requests@faa.gov.

(2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC.

(i) Additional Information

(1) Eurocopter Alert Service Bulletin (ASB) No. 05A003, Revision 2, dated July 16, 2003; Eurocopter ASB No. 05A003, Revision 3, dated May 11, 2004; and Eurocopter Service Bulletin No. 71–003, Revision 1, dated July 18, 2002; which are not incorporated by reference, contain additional information about the subject of this final rule. For Eurocopter service information identified in this final rule, contact Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at http:// www.airbushelicopters.com/techpub. You may review a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177.

(2) The subject of this AD is addressed in Direction Generale de L’Aviation Civile (DGAC) AD No. F–2003–325 R1, Revision 1, dated May 12, 2004. You may view the DGAC AD on the Internet at http:// www.regulations.gov in Docket No. FAA–

2014–0105.
(j) Subject

Joint Aircraft Service Component (JASC) Code: 6310, Engine/Transmission Coupling— Coupling Tube, Engine Mount, and Engine
Mount Base.
(k) Material Incorporated by Reference

(1) The Director of the Federal Register approved the incorporation by reference of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise.

(i) Eurocopter Alert Service Bulletin No. 04A005, Revision 0, dated July 16, 2003.

(ii) Eurocopter Service Bulletin No. 71– 005, Revision 0, dated May 14, 2004.

(3) For Eurocopter service information identified in this final rule, contact Airbus Helicopters, 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at http://www.airbushelicopters.com/techpub.

(4) You may view this service information at FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. For information on the availability of this material at the FAA, call (817) 222–5110.

(5) You may view this service information that is incorporated by reference 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/cfr/ibrlocations.html.

Issued in Fort Worth, Texas, on June 9,

2016. Scott A. Horn, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.

[FR Doc. 2016–14467 Filed 6–21–16; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 95**

**[Docket No. 31084; Amdt. No. 527]**

**IFR Altitudes; Miscellaneous Amendments** 

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Final rule. **SUMMARY :**  This amendment adopts miscellaneous amendments to the required IFR (instrument flight rules) altitudes and changeover points for certain Federal airways, jet routes, or direct routes for which a minimum or maximum en route authorized IFR altitude is prescribed. This regulatory action is needed because of changes occurring in the National Airspace System. These changes are designed to provide for the safe and efficient use of the navigable airspace under instrument conditions in the affected areas.

**DATES :**  Effective 0901 UTC, July 21,

2016.

**FOR FURTHER INFORMATION CONTACT :**  Richard A. Dunham, Flight Procedure Standards Branch (AMCAFS–420), Flight Technologies and Programs Division, Flight Standards Service, Federal Aviation Administration, Mike Monroney Aeronautical Center, 6500 South MacArthur Blvd., Oklahoma City, OK 73169 (Mail Address: P.O. Box 25082 Oklahoma City, OK 73125) telephone: (405) 954–4164.

**SUPPLEMENTARY INFORMATION :**  This amendment to part 95 of the Federal Aviation Regulations (14 CFR part 95) amends, suspends, or revokes IFR altitudes governing the operation of all aircraft in flight over a specified route or any portion of that route, as well as the changeover points (COPs) for Federal airways, jet routes, or direct routes as prescribed in part 95.

The Rule

The specified IFR altitudes, when used in conjunction with the prescribed changeover points for those routes, ensure navigation aid coverage that is adequate for safe flight operations and free of frequency interference. The reasons and circumstances that create the need for this amendment involve matters of flight safety and operational efficiency in the National Airspace System, are related to published aeronautical charts that are essential to the user, and provide for the safe and efficient use of the navigable airspace. In addition, those various reasons or circumstances require making this amendment effective before the next scheduled charting and publication date of the flight information to assure its timely availability to the user. The effective date of this amendment reflects those considerations. In view of the close and immediate relationship between these regulatory changes and safety in air commerce, I find that notice and public procedure before adopting this amendment are impracticable and contrary to the public interest and that good cause exists for making the