14378 Federal Register / Vol. 73, No. 53 / Tuesday, March 18, 2008 / Rules and Regulations 

2008–06–19 Honeywell International Inc. 

(formerly AlliedSignal Inc. and Garrett 

Turbine Engine Co.): Amendment 39–

15431. Docket No. FAA–2007–29092; 

Directorate Identifier 2007–NE–30–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective April 22, 2008. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Honeywell 

International Inc. ATF3–6–4C, ATF3–6A–3C, 

and ATF3–6A–4C turbofan engines equipped 

with part number (P/N) 3002070–1 low 

pressure compressor (LPC) Aft shaft. These 

engines are installed on, but not limited to, 

Dassault Aviation Fan Jet Falcon Series G 

(Falcon 20G/HU25), and Dassault Aviation 

Mystere-Falcon 200 airplanes. 

Unsafe Condition 

(d) This AD results from reports of eight 

LPC aft shafts found cracked during 

fluorescent penetrant inspection (FPI). We 

are issuing this AD to prevent uncoupling 

and overspeed of the low pressure turbine, 

which could result in uncontained engine 

failure and damage to the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified in Table 1 

and Table 2 of this AD, unless the actions 

have already been done. 

TABLE 1.—ATF3–6A–4C TURBOFAN ENGINES, LPC AFT SHAFT REPLACEMENT COMPLIANCE SCHEDULE

For ATF3–6A–4C turbofan engines, if the 

cycles-since-new (CSN) on the effective date of 

this AD are: 

Then replace the LPC Aft shaft: 

(1) 6,500 or more CSN ....................................... Within an additional 100 cycles-in-service (CIS). 

(2) 5,000 to 6,499 CSN ...................................... Within an additional 800 CIS, but not more than 6,600 CSN, whichever occurs first. 

(3) 4,000 to 4,999 CSN ...................................... Within an additional 1,500 CIS, but not more than 5,800 CSN, whichever occurs first. 

(4) Fewer than 4,000 CSN ................................. Within an additional 2,000 CIS, but not more than 5,500 CSN, whichever occurs first. 

TABLE 2.—ATF3–6–4C AND ATF3–6A–3C TURBOFAN ENGINES, LPC AFT SHAFT REPLACEMENT COMPLIANCE

SCHEDULE

For ATF3–6–4C and ATF3–6A–3C turbofan 

engines, if the CSN on the effective date of this 

AD are: 

Then replace the LPC Aft shaft: 

(1) 4,400 or more CSN ....................................... Within an additional 100 CIS. 

(2) 3,600 to 4,399 CSN ...................................... Within an additional 500 CIS, but not more than 4,500 CSN, whichever occurs first. 

(3) 3,300 to 3,599 CSN ...................................... Within an additional 700 CIS, but not more than 4,100 CSN, whichever occurs first. 

(4) Fewer than 3,300 CSN ................................. Within an additional 1,000 CIS, but not more than 4,000 CSN, whichever occurs first. 

LPC Aft Shaft Replacement 

(f) Using the compliance schedule in Table 

1 or Table 2 of this AD as applicable, remove 

the LPC aft shaft, P/N 3002070–1, from 

service, and install a serviceable LPC aft 

shaft. 

Definition 

(g) For the purpose of this AD, a 

serviceable LPC aft shaft is an aft shaft with 

a P/N not referenced in this AD. 

Alternative Methods of Compliance 

(h) The Manager, Los Angeles Aircraft 

Certification Office, has the authority to 

approve alternative methods of compliance 

for this AD if requested using the procedures 

found in 14 CFR 39.19. 

Related Information 

(i) Honeywell International Inc. Service 

Bulletin No. ATF3–72–6240, Revision 1, 

dated May 14, 2007, pertains to the subject 

of this AD. 

(j) Contact Joseph Costa, Aerospace 

Engineer, Los Angeles Aircraft Certification 

Office, FAA, Transport Airplane Directorate, 

3960 Paramount Blvd., Lakewood CA 90712–

4137; e-mail: joseph.costa@faa.gov; 

telephone: (562) 627–5246; fax: (562) 627–

5210, for more information about this AD. 

Material Incorporated by Reference 

(k) None. 

Issued in Burlington, Massachusetts, on 

March 10, 2008. 

Robert J. Ganley, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E8–5274 Filed 3–17–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–0216; Directorate 

Identifier 2007–NM–122–AD; Amendment 

39–15435; AD 2008–06–23] 

RIN 2120–AA64 

Airworthiness Directives; McDonnell 

Douglas Model DC–8–55, DC–8F–54, 

and DC–8F–55 Airplanes; and Model 

DC–8–60, DC–8–70, DC–8–60F, and 

DC–8–70F Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) 

that applies to certain McDonnell 

Douglas Model DC–8–55, DC–8F–54, 

and DC–8F–55 airplanes; and Model 

DC–8–60, DC–8–70, DC–8–60F, and 

DC–8–70F series airplanes. The existing 

AD currently requires a one-time 

inspection for previous repairs of the aft 

fuselage skin panel at the longeron 28 

skin splice, repetitive inspections for 

cracks of the same area, and related 

investigative and corrective actions. The 

existing AD also provides optional 

actions for extending the repetitive 

inspection intervals. This new AD redefines and more clearly describes the 

optional actions for extending the 

repetitive inspection intervals. This AD 

results from our determination that the 

inspections and actions described in the 

existing AD do not adequately address 

the unsafe condition. We are issuing 

this AD to detect and correct cracks in 

the aft fuselage skin at the longeron 28 

skin splice, which could lead to loss of 

structural integrity of the aft fuselage, 

resulting in rapid decompression of the 

airplane. 

DATES: This AD becomes effective April 

22, 2008. 

The incorporation by reference of 

certain publications listed in the AD 

was approved previously by the Director 


rwilkins on PROD1PC63 with PROPOSALS
Federal Register / Vol. 73, No. 53 / Tuesday, March 18, 2008 / Rules and Regulations 14379 

of the Federal Register as of February 

28, 2007 (72 FR 3044, January 24, 2007). 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Long Beach 

Division, 3855 Lakewood Boulevard, 

Long Beach, California 90846, 

Attention: Data and Service 

Management, Dept. C1–L5A (D800–

0024). 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (telephone 800–647–5527) 

is the 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: Jon 

Mowery, Aerospace Engineer, Airframe 

Branch, ANM–120L, FAA, Los Angeles 

Aircraft Certification Office, 3960 

Paramount Boulevard, Lakewood, 

California 90712–4137; telephone (562) 

627–5322; fax (562) 627–5210. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 2007–02–02, amendment 

39–14889 (72 FR 3044, January 24, 

2007). The existing AD applies to 

certain McDonnell Douglas Model DC–

8–55, DC–8F–54, and DC–8F–55 

airplanes; and Model DC–8–60, DC–8–

70, DC–8–60F, and DC–8–70F series 

airplanes. That NPRM was published in 

the Federal Register on November 21, 

2007 (72 FR 65471). That NPRM 

proposed to continue to require a onetime inspection for previous repairs of 

the aft fuselage skin panel at the 

longeron 28 skin splice, repetitive 

inspections for cracking of the same 

area, and related investigative and 

corrective actions. That NPRM also 

proposed to re-define and more clearly 

describe the optional actions for 

extending the repetitive inspection 

intervals. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comment that was 

received on the NPRM. 

Request To Give Credit for Prior 

Submission of Inspection Findings 

UPS agrees with the intent of the 

NPRM. UPS requests, however, that we 

revise paragraphs (k)(1) and (k)(2) of the 

NPRM to specify submitting positive 

findings ‘‘unless previously submitted 

to Boeing for compliance with AD 

2007–02–02.’’ UPS asserts that this 

would allow all alternative methods of 

compliance (AMOCs) that apply to AD 

2007–02–02 to be applicable to this new 

AD ‘‘as per paragraph (k)(4) [sic].’’ UPS 

states that this will prevent operators 

from having to submit data already 

submitted previously for AD 2007–02–

02, and again requesting AMOC 

approval. 

We do not agree with this request. 

Operators are always given credit for 

work previously performed according to 

the existing AD by means of the phrase 

in the compliance paragraph of this AD 

that states, ‘‘Required * * * unless the 

actions have already been done.’’ In 

addition, paragraph (l)(4) of this AD 

(rather than paragraph (k)(4) as specified 

by the commenter) states that AMOCs 

approved for compliance with AD 

2007–02–02 are acceptable for 

compliance with the corresponding 

provisions of this AD. For these reasons, 

no change is needed to the AD in this 

regard. 

Conclusion 

We have carefully reviewed the 

available data, including the comment 

that has been received, and determined 

that air safety and the public interest 

require adopting the AD as proposed. 

Costs of Compliance 

There are approximately 508 

airplanes of the affected design in the 

worldwide fleet. The FAA estimates that 

244 airplanes of U.S. registry are 

affected by this AD. The average labor 

rate is $80 per work hour. This AD adds 

no additional costs; however, we are 

repeating the costs from AD 2007–02–02 

for the convenience of affected 

operators. 

ESTIMATED COSTS

Action Work hours Cost per airplane Fleet cost 

Initial inspection for doubler installation ......................... 2 to 4 ................................. $160 to $320 ..................... $39,040 to $78,080. 

Repetitive inspections (per inspection cycle) ................. 2 to 8 ................................. $160 to $640 ..................... $39,040 to $156,160. 

Repair ............................................................................. 164 to 184 ......................... $13,120 to $14,720 ........... $3,201,280 to $3,591,680. 

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); 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. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 


rwilkins on PROD1PC63 with PROPOSALS
14380 Federal Register / Vol. 73, No. 53 / Tuesday, March 18, 2008 / Rules and Regulations 

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 Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendment 39–14889 (72 

FR 3044, January 24, 2007) and by 

adding the following new airworthiness 

directive (AD): 

2008–06–23 McDonnell Douglas: 

Amendment 39–15435. Docket No. 

FAA–2007–0216; Directorate Identifier 

2007–NM–122–AD. 

Effective Date 

(a) This AD becomes effective April 22, 

2008. 

Affected ADs 

(b) This AD supersedes AD 2007–02–02. 

Applicability 

(c) This AD applies to McDonnell Douglas 

Model DC–8–55, DC–8F–54, DC–8F–55, DC–

8–61, DC–8–62, DC–8–63, DC–8–61F, DC–8–

62F, DC–8–63F, DC–8–71, DC–8–72, DC–8–

73, DC–8–71F, DC–8–72F, and DC–8–73F 

airplanes, certificated in any category; as 

identified in Boeing Alert Service Bulletin 

DC8–53A080, dated June 22, 2004. 

Unsafe Condition 

(d) This AD results from our determination 

that the inspections and actions described in 

the existing AD do not adequately address 

the unsafe condition. We are issuing this AD 

to detect and correct cracks in the aft fuselage 

skin at the longeron 28 skin splice, which 

could lead to loss of structural integrity of the 

aft fuselage, resulting in rapid decompression 

of the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Requirements of AD 2007–02–02 

One-Time Inspection for Previous Repairs 

(f) For all airplanes: At the applicable time 

in paragraph (f)(1) or (f)(2) of this AD, do a 

general visual inspection to determine if 

there are previous repairs of the aft fuselage 

skin panel at the longeron 28 skin splice; in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

DC8–53A080, dated June 22, 2004. Then do 

the applicable actions specified in 

paragraphs (g) and (h) of this AD. 

(1) For airplanes that have accumulated 

fewer than 24,000 total flight cycles as of 

February 28, 2007 (the effective date of AD 

2007–02–02): Within 24 months after 

February 28, 2007, or prior to accumulating 

24,000 total flight cycles, whichever occurs 

later. 

(2) For airplanes that have accumulated 

24,000 total flight cycles or more as of 

February 28, 2007: Within 12 months after 

February 28, 2007. 

Note 1: For the purposes of this AD, a 

general visual inspection is: ‘‘A visual 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made from within touching 

distance unless otherwise specified. A mirror 

may be necessary to ensure visual access to 

all surfaces in the inspection area. This level 

of inspection is made under normally 

available lighting conditions such as 

daylight, hangar lighting, flashlight, or 

droplight and may require removal or 

opening of access panels or doors. Stands, 

ladders, or platforms may be required to gain 

proximity to the area being checked.’’

Repetitive Inspections for Areas That Do Not 

Have a Previous Repair 

(g) For areas that do not have a previous 

repair: Before further flight after the initial 

inspection in paragraph (f) of this AD, do 

general visual and high-frequency eddy 

current (HFEC) inspections for discrepancies 

at longeron 28 between the bolted connection 

of the tail section to forward of the flat aft 

pressure bulkhead, on both the left and right 

sides, and do all applicable related 

investigative and corrective actions before 

further flight. Do all actions in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin DC8–53A080, 

dated June 22, 2004. Repeat the general 

visual and HFEC inspections thereafter at 

intervals not to exceed 2,000 flight cycles 

until an optional action in paragraph (i) of 

this AD is accomplished. 

Repetitive Inspections and Repair for Areas 

That Have a Previous Repair 

(h) For areas that have a previous repair: 

Within 24 months after accomplishing the 

initial inspection in paragraph (f) of this AD, 

remove the previous repair(s), and install a 

local repair, in accordance with Boeing DC–

8 Service Rework Drawing SR08530032, 

dated January 13, 2004, including Boeing 

Parts List PL SR08530032, dated January 7, 

2004, Boeing Advance Engineering Order, 

Advanced Drawing Change A, dated April 1, 

2004, and Boeing Engineering Order, dated 

January 13, 2004. Do the inspections in 

paragraph (j) of this AD thereafter at the 

applicable interval specified in paragraph 

(j)(1) or (j)(2) of this AD. 

New Requirements of This AD 

Optional Modification/Repair 

(i) Installing a full-length preventive 

modification, doing a full-length repair, or 

doing a local repair, in accordance with 

Boeing DC–8 Service Rework Drawing 

SR08530032, dated January 13, 2004, 

including Boeing Parts List PL SR08530032, 

dated January 7, 2004; Boeing Advance 

Engineering Order, Advanced Drawing 

Change A, dated April 1, 2004; and Boeing 

Engineering Order, dated January 13, 2004; 

ends the repetitive inspection intervals 

specified in paragraph (g) of this AD. 

Extended Repetitive Inspection Intervals 

(j) After removing the previous repair(s) 

and doing the actions specified in paragraph 

(h) of this AD or doing any optional repair 

or modification described in paragraph (i) of 

this AD: Do the actions described in 

paragraph (j)(1) or (j)(2) of this AD as 

applicable, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin DC8–53A080, dated June 22, 

2004. If any discrepancy is discovered during 

any inspection required by this paragraph, 

before further flight, repair the discrepancy 

using a method approved in accordance with 

the procedures specified in paragraph (l) of 

this AD. 

(1) For areas that have been repaired on 

airplanes that do have internal finger 

doublers installed: Within 30,000 flight 

cycles after doing the optional repair or 

modification, do a general visual inspection 

for discrepancies along all four external 

edges of the doublers. Repeat the inspection 

thereafter at intervals not to exceed 5,000 

flight cycles. 

(2) For areas that have been repaired on 

airplanes that do not have internal finger 

doublers installed: Do the actions specified 

in paragraph (j)(2)(i) or (j)(2)(ii) of this AD, 

as applicable. 

(i) For any repair that is 12 inches or less 

along the longeron: Within 15,000 flight 

cycles after removing the previous repair(s) 

and doing the actions specified in paragraph 

(h) of this AD or doing any optional repair 

or modification specified in paragraph (i) of 

this AD, do a general visual inspection for 

discrepancies along all four external edges of 

the doublers. Repeat the general visual 

inspection thereafter at intervals not to 

exceed 5,000 flight cycles. 

(ii) For any repair that is greater than 12 

inches in length along the longeron: Within 

15,000 flight cycles after removing the 

previous repair(s) and doing the actions 

specified in paragraph (h) of this AD or doing 

any optional repair or modification specified 

in paragraph (i) of this AD, do a lowfrequency eddy current (LFEC) inspection for 

discrepancies along all four external edges of 

the doublers. Repeat the LFEC inspection 

thereafter at intervals not to exceed 10,000 

flight cycles. 

Reporting of Results 

(k) Submit a report of positive findings of 

the inspections required by paragraphs (g) 

and (j) of this AD to Boeing Commercial 

Airplanes, Manager, Structure/Payloads, 

Technical and Fleet Support, Service 

Engineering/Commercial Aviation Services, 

Long Beach Division, 3855 Lakewood 

Boulevard, Long Beach, California 90846, at 

the applicable time specified in paragraph 

(k)(1) or (k)(2) of this AD. The report must 

include the inspection results, a description 

of any discrepancies found, the airplane 


rwilkins on PROD1PC63 with PROPOSALS
Federal Register / Vol. 73, No. 53 / Tuesday, March 18, 2008 / Rules and Regulations 14381 

fuselage number, and the total number of 

landings and flight hours on the airplane. 

Information collection requirements 

contained in this AD have been approved by 

the Office of Management and Budget (OMB) 

under the provisions of the Paperwork 

Reduction Act (44 U.S.C. 3501 et seq.) and 

have been assigned OMB Control Number 

2120–0056. 

(1) For any inspection accomplished after 

the effective date of this AD: Submit the 

report within 30 days after performing the 

inspection. 

(2) For any inspection accomplished prior 

to the effective date of this AD: Submit the 

report within 30 days after the effective date 

of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(l)(1) The Manager, Los Angeles Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested in accordance with the procedures 

found in 14 CFR 39.19. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by an 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization who has been 

authorized by the Manager, Los Angeles 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane and 14 

CFR 25.571, Amendment 45, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved previously in 

accordance with AD 2007–02–02, are 

approved as AMOCs for the corresponding 

provisions of this AD. 

Material Incorporated by Reference 

(m) You must use Boeing Alert Service 

Bulletin DC8–53A080, dated June 22, 2004; 

and Boeing DC–8 Service Rework Drawing 

SR08530032, dated January 13, 2004, 

including Boeing Parts List PL SR08530032, 

dated January 7, 2004, Boeing Advance 

Engineering Order, Advanced Drawing 

Change A, dated April 1, 2004, and Boeing 

Engineering Order, dated January 13, 2004; as 

applicable, to perform the actions that are 

required by this AD, unless the AD specifies 

otherwise. 

(1) On February 28, 2007 (72 FR 3044, 

January 24, 2007), the Director of the Federal 

Register approved the incorporation by 

reference of these documents. 

(2) Contact Boeing Commercial Airplanes, 

Long Beach Division, 3855 Lakewood 

Boulevard, Long Beach, California 90846, 

Attention: Data and Service Management, 

Dept. C1–L5A (D800–0024), for a copy of this 

service information. You may review copies 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue, SW., Renton, 

Washington; 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/ 

cfr/ibr-locations.html. 

Issued in Renton, Washington, on March 9, 

2008. 

Stephen P. Boyd, 

Assistant Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E8–5295 Filed 3–17–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 95 

[Docket No. 30599; Amdt. No. 473] 

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 Date: 0901 UTC, April 

10, 2008. 

FOR FURTHER INFORMATION CONTACT: 

Donald P. Pate, 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 

amendment effective in less than 30 

days. 

Conclusion 

The FAA has determined that this 

regulation only involves an established 

body of technical regulations for which 

frequent and routine amendments are 

necessary to keep them operationally 

current. It, therefore—(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) 

does not warrant preparation of a 

regulatory evaluation as the anticipated 

impact is so minimal. For the same 

reason, the FAA certifies that this 

amendment will not have a significant 

economic impact on a substantial 

number of small entities under the 

criteria of the Regulatory Flexibility Act. 

List of Subjects in 14 CFR Part 95 

Airspace, Navigation (air). 

Issued in Washington, DC on March 11, 

2008. 

James J. Ballough, 

Director, Flight Standards Service. 

Adoption of the Amendment 

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

part 95 of the Federal Aviation 

Regulations (14 CFR part 95) is 

amended as follows effective at 0901 

UTC, April 10, 2008. 


rwilkins on PROD1PC63 with PROPOSALS