64164 Federal Register / Vol. 78, No. 208 / Monday, October 28, 2013 / Rules and Regulations 

15, 2011; or Airbus Service Bulletin A320– 

35–1058, dated June 15, 2011; as applicable; 

are excluded from the requirements of 

paragraph (g) of this AD, unless an oxygen 

container with a part number listed in 

paragraph (g)(1)(i) of this AD and a serial 

number listed in paragraph (g)(1)(ii) of this 

AD is installed. 

Note 1 to paragraph (g) of this AD: The 

oxygen container assemblies listed in 

paragraph (g)(1)(i) of this AD and paragraph 

(g)(1)(ii) of this AD are B/E Aerospace 

products with the mark ‘‘B/E AEROSPACE’’ 

on the identification plate. 

(h) Parts Installation Limitation 

As of the effective date of this AD, no 

person may install, on any airplane, an 

oxygen container with a part number listed 

in paragraph (g)(1)(i) of this AD, and serial 

number listed in paragraph (g)(1)(ii) of this 

AD, unless the oxygen container has been 

modified according to Airbus Service 

Bulletin A320–35–1049, dated June 15, 2011; 

Airbus Service Bulletin A320–35–1053, 

dated June 15, 2011; Airbus Service Bulletin 

A320–35–1054, dated June 15, 2011; Airbus 

Service Bulletin A320–35–1055, dated June 

15, 2011; Airbus Service Bulletin A320–35– 

1056, dated June 15, 2011; Airbus Service 

Bulletin A320–35–1057, dated June 15, 2011; 

or Airbus Service Bulletin A320–35–1058, 

dated June 15, 2011; as applicable. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1405; fax (425) 227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

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) Airworthy Product: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer or other source, 

use these actions if they are FAA-approved. 

Corrective actions are considered FAAapproved if they are approved by the State 

of Design Authority (or their delegated 

agent). You are required to assure the product 

is airworthy before it is returned to service. 

(j) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information European 

Aviation Safety Agency Airworthiness 

Directive 2012–0055, dated April 3, 2012, for 

related information. You may examine the 

MCAI in the AD docket on the Internet at 

http://www.regulations.gov/

#!documentDetail;D=FAA-2013-0465-0002. 

(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. 

(i) Airbus Service Bulletin A320–35–1049, 

dated June 15, 2011. 

(ii) Airbus Service Bulletin A320–35–1053, 

dated June 15, 2011. 

(iii) Airbus Service Bulletin A320–35– 

1054, dated June 15, 2011. 

(iv) Airbus Service Bulletin A320–35– 

1055, dated June 15, 2011. 

(v) Airbus Service Bulletin A320–35–1056, 

dated June 15, 2011. 

(vi) Airbus Service Bulletin A320–35– 

1057, dated June 15, 2011. 

(vii) Airbus Service Bulletin A320–35– 

1058, dated June 15, 2011. 

(3) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

(4) You may review copies of the 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. 

(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 Renton, Washington, on 

September 17, 2013. 

Ross Landes, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–23909 Filed 10–25–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0303; Directorate 

Identifier 2012–NM–220–AD; Amendment 

39–17620; AD 2013–20–14] 

RIN 2120–AA64 

Airworthiness Directives; the Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

the Boeing Company Model 747–400 

and –400F series airplanes. This AD was 

prompted by a report of cracks on 

airplanes prior to line number 1308 in 

the forward and aft inner chords of the 

station (STA) 2598 bulkhead, and the 

bulkhead upper and lower webs. This 

AD requires, as applicable, repetitive 

high frequency eddy current (HFEC) and 

low frequency eddy current (LFEC) 

inspections for cracks in the splice 

fitting, support frame, forward and aft 

inner chords, floor support, bulkhead 

upper web on the upper left and right 

side of the bulkhead, and the bulkhead 

lower web on the lower left side of the 

bulkhead and repair if necessary; and 

repetitive post-repair inspections and 

repair if necessary. We are issuing this 

AD to detect and correct cracks in the 

splice fitting, support frame, floor 

support, forward and aft inner chords, 

and the bulkhead upper and lower webs 

of the STA 2598 bulkhead, which could 

adversely affect the structural integrity 

of the airplane. 

DATES:DATES: This AD is effective 

December 2, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 2, 2013. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https:// 

www.myboeingfleet.com. You may 

review copies of the referenced 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. 

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 (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. 


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Federal Register / Vol. 78, No. 208 / Monday, October 28, 2013 / Rules and Regulations 64165 

FOR FURTHER INFORMATION CONTACT: 

Nathan Weigand, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6428; fax: 

425–917–6590; email: 

Nathan.P.Weigand@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. The 

NPRM published in the Federal 

Register on April 12, 2013 (78 FR 

21854). The NPRM proposed to require, 

as applicable, repetitive HFEC and LFEC 

inspections for cracks in the splice 

fitting, support frame, forward and aft 

inner chords, floor support, bulkhead 

upper web on the upper left and right 

side of the bulkhead, and the bulkhead 

lower web on the lower left side of the 

bulkhead and repair if necessary; and 

repetitive post-repair inspections and 

repair if necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (78 FR 21854, 

April 12, 2013) and the FAA’s response 

to each comment. 

Request To Include the Lower Web in 

the Inspection of the Unrepaired 

Structure 

Boeing requested that we revise 

paragraph (g) of the NPRM (78 FR 

21854, April 12, 2013) to clarify that the 

inspection of the unrepaired structure 

includes the lower webs. Boeing stated 

that the inspections for the unrepaired 

structure include both the upper and 

lower bulkhead webs, but that 

paragraph (g)(2)(ii) of the NPRM (78 FR 

21854, April 12, 2013) specifies only the 

upper web. 

We agree with Boeing’s comment. For 

appropriate service information, the 

NPRM (78 FR 21854, April 12, 2013) 

referred to Boeing Alert Service Bulletin 

747–53A2815, dated November 8, 2012, 

which also describes procedures for 

inspecting the bulkhead lower web. We 

have clarified the inspection in 

paragraph (g)(2)(ii) of this AD by 

referring to Boeing Alert Service 

Bulletin 747–53A2815, dated November 

8, 2012, for specific inspection 

procedures and locations. 

Request To Revise the Unsafe Condition 

Boeing requested that, for clarity, the 

unsafe condition be revised to more 

specifically identify the location of 

potential cracking (i.e., the body station 

2598 bulkhead). 

We agree with Boeing’s request. We 

have revised the unsafe condition in the 

SUMMARY and paragraph (e) of this final 

rule to clarify the location of the 

bulkhead. 

Request To Clarify the Discussion 

Section 

Boeing requested clarification of the 

Discussion section in the NPRM (78 FR 

21854, April 12, 2013). Boeing stated 

that the Discussion does not mention 

cracks found in the splice fitting and 

incorrectly refers to the ‘‘cutout for the 

horizontal stabilizer rear spar.’’ 

We agree that the commenter’s 

proposed clarification provides a more 

accurate description of the report of 

cracks. However, the Discussion section 

is not carried over into the final rule; 

therefore, no change to this final rule is 

necessary in this regard. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

21854, April 12, 2013) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 21854, 

April 12, 2013). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 11 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Inspections ............................. 28 work-hours × $85 per hour 

= $2,380 per inspection 

cycle.

$0 $2,380 per inspection cycle ... $26,180 per inspection cycle. 

We estimate the following costs to do 

any necessary repairs and post-repair 

inspections that would be required 

based on the results of the inspection. 

We have no way of determining the 

number of aircraft that might need this 

repair: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Repair ........................................................................... 13 work-hours × $85 per hour = $1,105 ...................... $0 $1,105 

Post-repair Inspection ................................................... 12 work-hours × $85 per hour = $1,020 ...................... 0 1,020 

For any repairs that would be necessary 

based on the results of the post-repair 

inspection, we have not received 

definitive data that would enable us to 

provide cost estimates for that oncondition action. Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 


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64166 Federal Register / Vol. 78, No. 208 / Monday, October 28, 2013 / Rules and Regulations 

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 

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, 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 adding 

the following new airworthiness 

directive (AD): 

2013–20–14 The Boeing Company: 

Amendment 39–17620; Docket No. 

FAA–2013–0303; Directorate Identifier 

2012–NM–220–AD. 

(a) Effective Date 

This AD is effective December 2, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–400 and –400F series airplanes, 

certificated in any category, as identified in 

Boeing Alert Service Bulletin 747–53A2815, 

dated November 8, 2012. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by a report of 

cracks on airplanes prior to line number 1308 

in the forward and aft inner chords of the 

station (STA) 2598 bulkhead, and the 

bulkhead upper and lower webs. We are 

issuing this AD to detect and correct cracks 

in the splice fitting, support frame, floor 

support, forward and aft inner chords, and 

the bulkhead upper and lower webs of the 

STA 2598 bulkhead, which could adversely 

affect the structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) High Frequency Eddy Current (HFEC) 

and Low Frequency Eddy Current (LFEC) 

Inspections 

At the compliance time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 747–53A2815, dated 

November 8, 2012; except as provided by 

paragraph (h)(2) of this AD: Do HFEC and 

LFEC inspections, as applicable, for cracks in 

the splice fitting, support frame, floor 

support, forward and aft inner chords, the 

bulkhead upper web on the upper left and 

right side of the bulkhead, and the bulkhead 

lower web on the lower left side of the 

bulkhead, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2815, dated 

November 8, 2012. 

(1) If no cracking is found, repeat the 

applicable inspections specified in paragraph 

(g) of this AD, thereafter, at the applicable 

time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2815, dated November 8, 

2012. 

(2) If any cracking is found, do the actions 

specified in paragraphs (g)(2)(i) and (g)(2)(ii) 

of this AD. 

(i) Before further flight, do the applicable 

repair, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2815, dated 

November 8, 2012; except as provided by 

paragraph (h)(1) of this AD. 

(ii) At the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 747–53A2815, dated 

November 8, 2012, do HFEC and LFEC 

inspections for cracks in the unrepaired 

structure, and do an HFEC inspection for 

cracks in the repaired structure; as specified 

in and in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2815, dated 

November 8, 2012. 

(A) If no cracking is found, repeat the 

applicable HFEC and LFEC inspections 

specified in paragraph (g)(2)(ii) of this AD, 

thereafter, at the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 747–53A2815, dated 

November 8, 2012. 

(B) If any cracking is found, before further 

flight, repair using a method approved in 

accordance with the procedures specified in 

paragraph (i) of this AD. 

(h) Exceptions to the Service Information 

(1) If any crack is found during any 

inspection required by this AD, and Boeing 

Alert Service Bulletin 747–53A2815, dated 

November 8, 2012, specifies to contact 

Boeing for appropriate action: Before further 

flight, repair the crack using a method 

approved in accordance with the procedures 

specified in paragraph (i) of this AD. 

(2) Where Boeing Alert Service Bulletin 

747–53A2815, dated November 8, 2012, 

specifies a compliance time ‘‘after the 

original issue date of this service bulletin,’’ 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. 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 manager of the ACO, send it to the 

attention of the person identified in 

paragraph (j) of this AD. Information may be 

emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) 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. 

(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 the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(j) Related Information 

For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6428; fax: 425–917– 

6590; email: Nathan.P.Weigand@faa.gov. 


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Federal Register / Vol. 78, No. 208 / Monday, October 28, 2013 / Rules and Regulations 64167 

(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 the AD specifies otherwise. 

(i) Boeing Alert Service Bulletin 747– 

53A2815, dated November 8, 2012. 

(ii) Reserved. 

(3) For Boeing service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data & 

Services Management, P.O. Box 3707, MC 

2H–65, Seattle, WA 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; Internet https://

www.myboeingfleet.com. 

(4) You may review copies of the 

referenced 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. 

(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 Renton, Washington, on 

September 19, 2013. 

Ross Landes, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–24042 Filed 10–25–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 97 

[Docket No. 30923; Amdt. No. 3558] 

Standard Instrument Approach 

Procedures, and Takeoff Minimums 

and Obstacle Departure Procedures; 

Miscellaneous Amendments 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This rule establishes, amends, 

suspends, or revokes Standard 

Instrument Approach Procedures 

(SIAPs) and associated Takeoff 

Minimums and Obstacle Departure 

Procedures for operations at certain 

airports. These regulatory actions are 

needed because of the adoption of new 

or revised criteria, or because of changes 

occurring in the National Airspace 

System, such as the commissioning of 

new navigational facilities, adding new 

obstacles, or changing air traffic 

requirements. These changes are 

designed to provide safe and efficient 

use of the navigable airspace and to 

promote safe flight operations under 

instrument flight rules at the affected 

airports. 

DATES: This rule is effective October 28, 

2013. The compliance date for each 

SIAP, associated Takeoff Minimums, 

and ODP is specified in the amendatory 

provisions. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of October 28, 

2013. 

ADDRESSES: Availability of matters 

incorporated by reference in the 

amendment is as follows: 

For Examination— 

1. FAA Rules Docket, FAA 

Headquarters Building, 800 

Independence Avenue SW., 

Washington, DC 20591; 

2. The FAA Regional Office of the 

region in which the affected airport is 

located; 

3. The National Flight Procedures 

Office, 6500 South MacArthur Blvd., 

Oklahoma City, OK 73169 or, 

4. 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. 

Availability—All SIAPs and Takeoff 

Minimums and ODPs are available 

online free of charge. Visit http://

www.nfdc.faa.gov to register. 

Additionally, individual SIAP and 

Takeoff Minimums and ODP copies may 

be obtained from: 

1. FAA Public Inquiry Center (APA– 

200), FAA Headquarters Building, 800 

Independence Avenue SW., 

Washington, DC 20591; or 

2. The FAA Regional Office of the 

region in which the affected airport is 

located. 

FOR FURTHER INFORMATION CONTACT: 

Richard A. Dunham III, Flight Procedure 

Standards Branch (AFS–420), Flight 

Technologies and Programs Divisions, 

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 rule 

amends Title 14 of the Code of Federal 

Regulations, Part 97 (14 CFR part 97), by 

establishing, amending, suspending, or 

revoking SIAPS, Takeoff Minimums 

and/or ODPS. The complete regulators 

description of each SIAP and its 

associated Takeoff Minimums or ODP 

for an identified airport is listed on FAA 

form documents which are incorporated 

by reference in this amendment under 5 

U.S.C. 552(a), 1 CFR part 51, and 14 

CFR 97.20. The applicable FAA Forms 

are FAA Forms 8260–3, 8260–4, 8260– 

5, 8260–15A, and 8260–15B when 

required by an entry on 8260–15A. 

The large number of SIAPs, Takeoff 

Minimums and ODPs, in addition to 

their complex nature and the need for 

a special format make publication in the 

Federal Register expensive and 

impractical. Furthermore, airmen do not 

use the regulatory text of the SIAPs, 

Takeoff Minimums or ODPs, but instead 

refer to their depiction on charts printed 

by publishers of aeronautical materials. 

The advantages of incorporation by 

reference are realized and publication of 

the complete description of each SIAP, 

Takeoff Minimums and ODP listed on 

FAA forms is unnecessary. This 

amendment provides the affected CFR 

sections and specifies the types of SIAPs 

and the effective dates of the, associated 

Takeoff Minimums and ODPs. This 

amendment also identifies the airport 

and its location, the procedure, and the 

amendment number. 

The Rule 

This amendment to 14 CFR part 97 is 

effective upon publication of each 

separate SIAP, Takeoff Minimums and 

ODP as contained in the transmittal. 

Some SIAP and Takeoff Minimums and 

textual ODP amendments may have 

been issued previously by the FAA in a 

Flight Data Center (FDC) Notice to 

Airmen (NOTAM) as an emergency 

action of immediate flight safety relating 

directly to published aeronautical 

charts. The circumstances which 

created the need for some SIAP and 

Takeoff Minimums and ODP 

amendments may require making them 

effective in less than 30 days. For the 

remaining SIAPS and Takeoff 

Minimums and ODPS, an effective date 

at least 30 days after publication is 

provided. 

Further, the SIAPs and Takeoff 

Minimums and ODPS contained in this 

amendment are based on the criteria 

contained in the U.S. Standard for 

Terminal Instrument Procedures 

(TERPS). In developing these SIAPS and 

Takeoff Minimums and ODPs, the 

TERPS criteria were applied to the 

conditions existing or anticipated at the 

affected airports. Because of the close 

and immediate relationship between 

these SIAPs, Takeoff Minimums and 

ODPs, and safety in air commerce, I find 

that notice and public procedures before 


wreier-aviles on DSK5TPTVN1PROD with RULES