Federal Register / Vol. 79, No. 43 / Wednesday, March 5, 2014 / Rules and Regulations 12375 

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 it justifies 

making a regulatory distinction; 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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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): 

2014–04–11 Airbus Helicopters (Type 

Certificate Previously Held by 

Eurocopter France): Amendment 39– 

17770; Docket No. FAA–2013–0351; 

Directorate Identifier 2009–SW–049–AD. 

(a) Applicability 

This AD applies to Model AS350B, BA, B1, 

B2, B3, D; and AS355E, F, F1, F2, and N 

helicopters with a tail rotor (T/R) blade, part 

number (P/N) 355A12–0040–00, 355A–12– 

0040–01, 355A12–0040–02, 355A12–0040– 

03, 355A–12–0040–04, 355A12–0040–05, 

355A–12–0040–07, 355A–12–0040–08, all 

serial numbers (S/N); or P/N 355A12–0050– 

04, with a S/N 8400 through 9224, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

T/R blade trailing edge tab (tab) debonding. 

This condition could result in excessive 

vibration of the helicopter and loss of control 

of the helicopter. 

(c) Effective Date 

This AD becomes effective April 9, 2014. 

(d) 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. 

(e) Required Actions 

Within 100 hours time-in-service, install 

additional rivets on the trailing edge tab of 

each T/R blade, according to the following 

procedures, referencing Figure 1 of 

Eurocopter Alert Service Bulletin (ASB) No. 

64.00.05, Revision 2, dated February 15, 

2007, or ASB No. 64.00.04, Revision 2, dated 

February 15, 2007, whichever is applicable to 

your model helicopter: 

(1) Lightly sand the area to be drilled, 

using No. 80 then No. 220 sandpaper. 

(2) Locate and drill eight 2.5 mm-diameter 

holes (T): 4 holes (T) 12 mm from the existing 

rivets (E) and on the centerline of the existing 

rivets (E), then 4 holes (T) 24 mm from the 

existing rivets (E) and on the centerline of the 

existing rivets (E). 

(3) Deburr and clean the area around the 

drilled holes. 

(4) Install 8 rivets (1) on tab (L). Any 

installation direction of the rivets is 

permissible (pressure face or suction face of 

the T/R blade). 

(5) Inspect the tab for debonding. 

(i) If there is no debonding, paint the area. 

(ii) If there is debonding, replace the tab. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, Rotorcraft Directorate, FAA, may 

approve AMOCs for this AD. Send your 

proposal to: Gary Roach, Aviation Safety 

Engineer, Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 Meacham 

Blvd., Fort Worth, Texas 76137; telephone 

(817) 222–5110; email gary.b.roach@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. 

(g) Additional Information 

The subject of this AD is addressed in the 

Direction Generale de l’Aviation Civile 

(DGAC) AD No. F–2004–176 and AD No. F– 

2004–178, both dated November 10, 2004. 

You may view the DCAG ADs on the Internet 

at http://www.regulations.gov in Docket No. 

FAA–2013–0351. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6410, Tail rotor blades. 

(i) 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) Eurocopter Alert Service Bulletin 

64.00.05, Revision 2, dated February 15, 

2007. 

(ii) Eurocopter Alert Service Bulletin 

64.00.04, Revision 2, dated February 15, 

2007. 

(3) For Eurocopter service information 

identified in this AD, contact Airbus 

Helicopters, Inc., 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 

that is incorporated by reference at the FAA, 

Office of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

(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 February 

19, 2014. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–04285 Filed 3–4–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0830; Directorate 

Identifier 2013–NM–128–AD; Amendment 

39–17776; AD 2014–05–03] 

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 777 

airplanes. This AD was prompted by a 

report of cracking in the fuselage skin 

underneath the satellite communication 

(SATCOM) antenna adapter. This AD 

requires repetitive inspections of the 

visible fuselage skin and doubler if 

installed, for cracking, corrosion, and 

any indication of contact of a certain 

fastener to a bonding jumper, and repair 

if necessary. We are issuing this AD to 

detect and correct cracking and 

corrosion in the fuselage skin, which 

could lead to rapid decompression and 


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loss of structural integrity of the 

airplane. 

DATES: This AD is effective April 9, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of April 9, 2014. 

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 view 

this 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 by searching for 

and locating Docket No. FAA–2013– 

0830; 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 

Docket 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: 

Melanie Violette, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: (425) 917–6422; 

fax: (425) 917–6590; email: 

melanie.violette@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain The Boeing Company 

Model 777 airplanes. The NPRM 

published in the Federal Register on 

September 26, 2013 (78 FR 59293). The 

NPRM was prompted by a report of 

cracking in the fuselage skin underneath 

the satellite communication (SATCOM) 

antenna adapter. The NPRM proposed 

to require repetitive inspections of the 

visible fuselage skin and doubler if 

installed, for cracking, corrosion, and 

any indication of contact of a certain 

fastener to a bonding jumper, and repair 

if necessary. We are issuing this AD to 

detect and correct cracking and 

corrosion in the fuselage skin, which 

could lead to rapid decompression and 

loss of structural integrity of the 

airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (78 FR 59293, 

September 26, 2013) and the FAA’s 

response to each comment. 

Request To Revise Paragraph (h)(1) of 

the NPRM (78 FR 59293, September 26, 

2013) To Include Footnotes 

Boeing requested that paragraph (h)(1) 

of the NPRM (78 FR 59293, September 

26, 2013) be revised to include the 

footnotes to Tables 1, 5, and 9 of 

paragraph 1.E. ‘‘Compliance,’’ in 

addition to the ‘‘Questionnaire 

Column,’’ specified in Boeing Alert 

Service Bulletin 777–53A0068, dated 

June 12, 2013. Boeing stated that the 

statement, ‘‘at the time of the original 

issue date of this service bulletin’’ is not 

only used in the ‘‘Condition 

Questionnaire’’ column of Tables 1, 5, 

and 9 of paragraph 1.E. ‘‘Compliance,’’ 

but it is also used in the footnotes. 

We agree with Boeing’s request. We 

have revised paragraph (h)(1) of this 

final rule by removing the phrase ‘‘the 

‘Condition Questionnaire’ column in’’ 

so that the exception applies to the 

entire table including the footnotes. 

Request To Revise Paragraph (h)(1) of 

the NPRM (78 FR 59293, September 26, 

2013) To Include the Compliance Time 

Column of Tables 2 Through 12 

American Airlines (AA) requested 

that paragraph (h)(1) of the NPRM (78 

FR 59293, September 26, 2013) be 

revised to include exceptions for the 

footnotes in Tables 1, 5, and 9, and the 

compliance times in Tables 2, 3, 4, 6, 7, 

8, 10, 11, and 12, as specified in Boeing 

Alert Service Bulletin 777–53A0068, 

dated June 12, 2013. AA stated that 

paragraph (h)(1) of the NPRM creates 

exceptions to the service information in 

the ‘‘Condition Questionnaire’’ column 

in Tables 1, 5, and 9 of paragraph 1.E. 

‘‘Compliance’’ of Boeing Alert Service 

Bulletin 777–53A0068, dated June 12, 

2013, in that it allows a change in 

wording from ‘‘. . . at the time of the 

original issue of this service bulletin’’ to 

‘‘. . . as of the effective date of this 

AD.’’ AA stated that this exception 

should be allowed for Tables 2 through 

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

Boeing Alert Service Bulletin 777– 

53A0068, dated June 12, 2013. 

We partially agree with AA’s request. 

As stated previously, we have revised 

paragraph (h)(1) of this final rule to 

address the footnotes in Tables 1, 5, and 

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

Boeing Alert Service Bulletin 777– 

53A0068, dated June 12, 2013. However, 

paragraph (h)(2) of this final rule 

already provides the exception for 

certain compliance times for Tables 2, 3, 

4, 6, 7, 8, 10, 11, and 12, of paragraph 

1.E. ‘‘Compliance,’’ of Boeing Alert 

Service Bulletin 777–53A0068, dated 

June 12, 2013. Therefore, no change is 

necessary to the final rule in this regard. 

Request To Add a Terminating Action 

FedEx requested that a terminating 

action be added prior to the release of 

the final rule. FedEx stated that Boeing 

should revise Boeing Alert Service 

Bulletin 777–53A0068, dated June 12, 

2013, to include a terminating action. 

FedEx stated that although the initial 

inspection can be planned during a 

scheduled maintenance visit, the 

repetitive inspections will require 

additional, unscheduled, and out of 

service time. FedEx also stated that the 

terminating action would alleviate any 

additional maintenance, scheduled or 

otherwise. 

We disagree. We do not consider that 

delaying this action until after the 

release of new service information is 

warranted. We do not agree to delay this 

final rule while a terminating action is 

being developed due to the unsafe 

condition that exists. However, under 

the provisions of paragraph (i)(1) of this 

final rule, we will consider alternative 

methods of compliance if sufficient data 

are submitted to substantiate that the 

change would provide an acceptable 

level of safety. We have not changed 

this final rule 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 change 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 

59293, September 26, 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 59293, 

September 26, 2013). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 


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Costs of Compliance 

We estimate that this AD affects 120 

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 

Inspection ..... Up to 36 work-hours × $85 per 

hour = $3,060 per inspection 

cycle.

$0 Up to $3,060 per inspection cycle Up to $367,200 per inspection 

cycle. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified 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 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): 

2014–05–03 The Boeing Company: 

Amendment 39–17776; Docket No. 

FAA–2013–0830; Directorate Identifier 

2013–NM–128–AD. 

(a) Effective Date 

This AD is effective April 9, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 777–200, –200LR, –300, –300ER, and 

–777F series airplanes, certificated in any 

category, as identified in Boeing Alert 

Service Bulletin 777–53A0068, dated June 

12, 2013. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by a report of 

cracking in the fuselage skin underneath the 

satellite communication (SATCOM) antenna 

adapter. We are issuing this AD to detect and 

correct cracking and corrosion in the fuselage 

skin, which could lead to rapid 

decompression and loss of structural 

integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

(1) For Groups 1–4 airplanes, and Group 5, 

Configurations 3 and 4 airplanes, identified 

in Boeing Alert Service Bulletin 777– 

53A0068, dated June 12, 2013: Except as 

required by paragraphs (h)(1) and (h)(2) of 

this AD, within the applicable compliance 

times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 777–53A0068, dated June 12, 2013, 

do internal detailed and surface high 

frequency eddy current (HFEC) inspections 

of the visible fuselage skin, and doubler if 

installed, for cracking; do external detailed 

and surface HFEC inspections of the visible 

fuselage skin, and doubler if installed, for 

cracking, corrosion, and any indication that 

shows a contact of a certain fastener to a 

bonding jumper; and do all applicable 

repairs; in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 777–53A0068, dated June 

12, 2013, except as required by paragraph 

(h)(3) of this AD. Thereafter, repeat the 

inspections at the applicable intervals 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 777–53A0068, 

dated June 12, 2013. Do all applicable repairs 

before further flight. 

(2) For Group 5, Configurations 1, 2, and 

5 airplanes, identified in Boeing Alert 

Service Bulletin 777–53A0068, dated June 

12, 2013: No action is required by this AD. 

(h) Exceptions to the Service Information 

(1) Tables 1, 5, and 9 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 777–53A0068, dated June 12, 2013, 

refer to airplanes with certain conditions ‘‘at 

the time of the original issue date of this 

service bulletin.’’ For this AD, use ‘‘as of the 

effective date of this AD’’ instead of ‘‘at the 

time of the original issue date of this service 

bulletin.’’ 

(2) Where paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 777–53A0068, 

dated June 12, 2013, 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. 

(3) If any crack, corrosion, or indication 

that shows a contact of the fastener attaching 

the SATCOM lug adapter plate to the 

bonding plate is found during any inspection 

required by this AD, and Boeing Alert 

Service Bulletin 777–53A0068, dated June 

12, 2013, specifies to contact Boeing for 

repair instructions: Before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (i) of this AD. 


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(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 (i) 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 Melanie Violette, Aerospace 

Engineer, Airframe Branch, ANM 120S, FAA, 

Seattle Aircraft Certification Office, 1601 

Lind Avenue SW., Renton, WA 98057 3356; 

phone: (425) 917–6422; fax: (425) 917–6590; 

email: melanie.violette@faa.gov. 

(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 777– 

53A0068, dated June 12, 2013. 

(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 view this service information 

at 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 February 

18, 2014. 

Ross Landes, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–04547 Filed 3–4–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 97 

[Docket No. 30944; Amdt. No. 3578] 

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 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 March 5, 

2014. 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 March 5, 

2014. 

ADDRESSES: Availability of matter 

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 are available 

online free of charge. Visit 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 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 rule 

amends Title 14, Code of Federal 

Regulations, Part 97 (14 CFR part 97) by 

amending the referenced SIAPs. The 

complete regulatory description of each 

SIAP is listed on the appropriate FAA 

Form 8260, as modified by the National 

Flight Data Center (FDC)/Permanent 

Notice to Airmen (P–NOTAM), and is 

incorporated by reference in the 

amendment under 5 U.S.C. 552(a), 1 

CFR part 51, and § 97.20 of Title 14 of 

the Code of Federal Regulations. 

The large number of SIAPs, their 

complex nature, and the need for a 

special format make their verbatim 

publication in the Federal Register 

expensive and impractical. Further, 

airmen do not use the regulatory text of 

the SIAPs, but refer to their graphic 

depiction on charts printed by 

publishers of aeronautical materials. 

Thus, the advantages of incorporation 

by reference are realized and 

publication of the complete description 

of each SIAP contained in FAA form 

documents is unnecessary. This 

amendment provides the affected CFR 

sections and specifies the types of SIAP 

and the corresponding effective dates. 

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 as amended in the 

transmittal. For safety and timeliness of 

change considerations, this amendment 


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