Federal Register / Vol. 80, No. 83 / Thursday, April 30, 2015 / Rules and Regulations 24193 

impracticable, and good cause exists for 

adopting these special conditions upon 

publication in the Federal Register. The 

FAA is requesting comments to allow 

interested persons to submit views that 

may not have been submitted in 

response to the prior opportunities for 

comment described above. 

List of Subjects in 14 CFR Part 25 

Aircraft, Aviation safety, Reporting 

and recordkeeping requirements. 

The authority citation for these 

special conditions is as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701, 

44702, 44704. 

The Special Conditions 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the following special 

conditions are issued as part of the typecertification basis for the Bombardier 

Inc. Model BD–700–2A12 and BD–700– 

2A13 airplanes. 

Design Roll Maneuver Condition 

In lieu of compliance to § 25.349(a): 

The following conditions, speeds, and 

cockpit roll-control motions (except as 

the motions may be limited by pilot 

effort) must be considered in 

combination with an airplane load 

factor of zero and of two-thirds of the 

positive maneuvering factor used in 

design. In determining the resulting 

control-surface deflections, the torsional 

flexibility of the wing must be 

considered in accordance with 

§ 25.301(b): 

1. Bombardier Inc. must investigate 

conditions corresponding to steady 

rolling velocities. In addition, 

conditions corresponding to maximum 

angular acceleration must be 

investigated for airplanes with engines 

or other weight concentrations outboard 

of the fuselage. For the angular 

acceleration conditions, zero rolling 

velocity may be assumed in the absence 

of a rational time-history investigation 

of the maneuver. 

2. At VA, sudden movement of the 

cockpit roll control up to the limit is 

assumed. The position of the cockpit 

roll control must be maintained until a 

steady roll rate is achieved and then 

must be returned suddenly to the 

neutral position. 

3. At VC, the cockpit roll control must 

be moved suddenly and maintained so 

as to achieve a roll rate not less than 

that obtained in Special Condition 2, 

above. 

4. At VD, the cockpit roll control must 

be moved suddenly and maintained so 

as to achieve a roll rate not less than one 

third of that obtained in Special 

Condition 2, above. 

Issued in Renton, Washington, on April 17, 

2015. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–10102 Filed 4–29–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 25 

[Docket No. FAA–2014–1080; Special 

Conditions No. 25–582–SC] 

Special Conditions: Airbus Model 

A319–151n/171n, A320–251n/271n, and 

A321–251n/271n (SAneo) Series 

Airplanes; Transient Engine-Failure 

Loads 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final special conditions; request 

for comments. 

SUMMARY: These special conditions are 

issued for Airbus Model A319–151n/

171n, A320–251n/271n, and A321– 

251n/271n (collectively known as 

Single Aisle new engine option (SA 

neo)) series airplanes. These airplanes 

will have a novel or unusual design 

feature when compared to the state of 

technology envisioned in the 

airworthiness standards for transportcategory airplanes. This design feature 

is a new generation of high-bypass 

engines, and the potential loads 

resulting from extreme engine-failure 

conditions. 

The applicable airworthiness 

regulations do not contain adequate or 

appropriate safety standards for this 

design feature. These special conditions 

contain the additional safety standards 

that the Administrator considers 

necessary to establish a level of safety 

equivalent to that established by the 

existing airworthiness standards. 

DATES: This action is effective on Airbus 

on April 30, 2015. We must receive your 

comments by June 15, 2015. 

ADDRESSES: Send comments identified 

by docket number FAA–2014–1080 

using any of the following methods: 

• Federal eRegulations Portal: Go to 

http://www.regulations.gov/ and follow 

the online instructions for sending your 

comments electronically. 

• Mail: Send comments to Docket 

Operations, M–30, U.S. Department of 

Transportation (DOT), 1200 New Jersey 

Avenue SE., Room W12–140, West 

Building Ground Floor, Washington, DC 

20590–0001. 

• Hand Delivery or Courier: Take 

comments to Docket Operations in 

Room W12–140 of the West Building 

Ground Floor at 1200 New Jersey 

Avenue SE., Washington, DC, between 9 

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

Friday, except Federal holidays. 

• Fax: Fax comments to Docket 

Operations at 202–493–2251. 

Privacy: The FAA will post all 

comments it receives, without change, 

to http://www.regulations.gov/, 

including any personal information the 

commenter provides. Using the search 

function of the docket Web site, anyone 

can find and read the electronic form of 

all comments received into any FAA 

docket, including the name of the 

individual sending the comment (or 

signing the comment for an association, 

business, labor union, etc.). DOT’s 

complete Privacy Act Statement can be 

found in the Federal Register published 

on April 11, 2000 (65 FR 19477–19478), 

as well as at 

http://DocketsInfo.dot.gov/. 

Docket: Background documents or 

comments received may be read at 

http://www.regulations.gov/ at any time. 

Follow the online instructions for 

accessing the docket or go to Docket 

Operations in Room W12–140 of the 

West Building Ground Floor at 1200 

New Jersey Avenue SE., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

FOR FURTHER INFORMATION CONTACT: 

Todd Martin, FAA, ANM–115, 

Transport Airplane Directorate, Aircraft 

Certification Service, 1601 Lind Avenue 

SW., Renton, Washington 98057–3356; 

telephone 425–227–1178; facsimile 

425–227–1320. 

SUPPLEMENTARY INFORMATION: The FAA 

has determined that notice of, and 

opportunity for prior public comment 

on, these special conditions is 

unnecessary. 

The substance of these special 

conditions has been subject to the 

public comment process in several prior 

instances with no substantive comments 

received. The FAA therefore finds that 

good cause exists for making these 

special conditions effective upon 

publication in the Federal Register. 

Comments Invited 

We invite interested people to take 

part in this rulemaking by sending 

written comments, data, or views. The 

most helpful comments reference a 

specific portion of the special 

conditions, explain the reason for any 

recommended change, and include 

supporting data. 

We will consider all comments we 

receive by the closing date for 


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24194 Federal Register / Vol. 80, No. 83 / Thursday, April 30, 2015 / Rules and Regulations 

comments. We may change these special 

conditions based on the comments we 

receive. 

Background 

On February 29, 2012, Airbus applied 

for amended type certificate no. A28NM 

for their new Model SAneo series 

airplanes. Later, Airbus requested, and 

the FAA approved, an extension to the 

application date for FAA type 

certification to June 30, 2012. 

The Airbus Model SAneo series 

airplanes are derivatives of the A319– 

100, A320–200, and A321–200 series 

airplanes equipped with SharkletsTM

(large winglets). The changes include 

installation of new CFMTM LEAPTM A 

engines on the A319–151n, A320–251n, 

and A321–251n series airplanes, and 

installation of new Pratt & Whitney PW– 

1100G engines on the A319–171n, 

A320–271n, and A321–271n series 

airplanes with larger fan diameters and 

reduced fuel consumption as compared 

to the current engines. The changes also 

include new nacelles, new pylons, new 

engine mounts, new bleed-air systems, 

structural reinforcements, software 

changes for the bleed-air system, an 

auto-flight system, an indicating and 

recording system, flight-warning and 

flight-control computers, and small 

changes to certified weights. 

The existing regulations are 

inadequate because the new high-bypass 

fan engines of the Airbus Model SAneo 

series airplanes can cause more damage 

in a failure event than could the 

previous engines. 

Type Certification Basis 

The certification basis for the SAneo 

series airplanes is the certification basis 

for the A319–100, A320–200 and A321– 

200 series airplanes with Sharklets, as 

defined in type-certificate data sheet 

A28NM for components or areas not 

affected by the SAneo change; and 

sections of 14 CFR part 25 as amended 

by Amendments 25–1 through 25–136 

(i.e., the amendment in effect on the 

date of the new reference date of 

application, June 30, 2012) applied to 

the components and areas affected by 

the SAneo change. Under the provisions 

of § 21.101, these regulations will be 

incorporated into type certificate no. 

A28NM after type certification approval 

of the Airbus Model SAneo series 

airplanes. 

In addition, the certification basis 

includes certain special conditions, 

exemptions, or later amended sections 

of the applicable part that are not 

relevant to these special conditions. 

If the Administrator finds that the 

applicable airworthiness regulations 

(i.e., 14 CFR part 25) do not contain 

adequate or appropriate safety standards 

for the Airbus Model SAneo series 

airplane because of a novel or unusual 

design feature, special conditions are 

prescribed under § 21.16. 

Special conditions are initially 

applicable to the model for which they 

are issued. Should the type certificate 

for that model be amended later to 

include any other model that 

incorporates the same novel or unusual 

design feature, these special conditions 

would also apply to the other model 

under § 21.101. 

In addition to the applicable 

airworthiness regulations and special 

conditions, the Airbus Model SAneo 

series airplanes must comply with the 

fuel-vent and exhaust-emission 

requirements of 14 CFR part 34, and the 

noise certification requirements of 14 

CFR part 36. 

The FAA issues special conditions, as 

defined in 14 CFR 11.19, under § 11.38, 

and they become part of the type 

certification basis under § 21.17(a)(2). 

Novel or Unusual Design Features 

The Airbus Model SAneo series 

airplanes will incorporate the following 

novel or unusual design feature: 

Engines with large, high-bypass fans 

capable of producing much higher 

failure loads than previous engine 

designs. 

The Airbus Model SAneo series 

airplanes therefore require additional 

dynamic-load analyses to assess the 

most severe engine-failure events. The 

loads resulting from these conditions 

would be considered as ultimate loads, 

with an additional safety factor applied 

to the airframe-supporting structure. 

Discussion 

The size, configuration, and failure 

modes of jet engines has changed 

considerably from those envisioned in 

§ 25.361(b), when the engine-seizure 

requirement was first adopted. Engines 

have become larger and are now 

designed with large, high-bypass fans 

capable of producing much higher 

failure loads. Relative to the engine 

configurations that existed when the 

rule was developed in 1957, the present 

generation of engines are sufficiently 

different and novel to justify special 

conditions for Model SAneo series 

airplanes and related future airplane 

models. Service history has shown that 

the engine-failure events that tend to 

cause the most severe loads are fanblade failures, and these events occur 

much less frequently than the typical 

‘‘limit’’ load condition. 

To maintain the level of safety 

envisioned by § 25.361(b), more 

comprehensive criteria are required for 

the new generation of high-bypass 

engines. These special conditions would 

distinguish between the more-common 

engine-failure event and those rare 

events resulting from structural failures. 

The more-common events would 

continue to be treated as static torque 

limit-load conditions. The more-severe 

events resulting from extreme enginefailure conditions (such as loss of a full 

fan blade at redline speed) would be 

treated as full dynamic-load conditions. 

These would be considered ultimate 

loads and include all transient loads 

associated with the event. An additional 

safety factor would be applied to the 

more-critical airframe supporting 

structure. 

The regulatory authorities and 

industry developed a standardized 

requirement in the Aviation Rulemaking 

Advisory Committee (ARAC) forum. 

The technical aspects of this 

requirement have been agreed upon, 

and have been accepted by, the ARAC 

Loads and Dynamics Harmonization 

Working Group. These special 

conditions reflect the ARAC 

recommendation and are essentially 

harmonized with the corresponding 

EASA Certification Specifications (CS) 

25. In addition, the ARAC 

recommendation includes 

corresponding advisory material that is 

incorporated into CS–25. This advisory 

material is considered an acceptable 

means of compliance to the special 

conditions. 

These special conditions contain the 

additional safety standards that the 

Administrator considers necessary to 

establish a level of safety equivalent to 

that established by the existing 

airworthiness standards. 

Applicability 

As discussed above, these special 

conditions apply to the Airbus Model 

SAneo series airplanes. Should Airbus 

apply later for a change to the type 

certificate to include another model 

incorporating the same novel or unusual 

design feature, these special conditions 

would apply to that model as well. 

Conclusion 

This action affects only certain novel 

or unusual design features on the Airbus 

Model SAneo series airplanes. It is not 

a rule of general applicability. 

List of Subjects in 14 CFR Part 25 

Aircraft, Aviation safety, Reporting 

and recordkeeping requirements. 

The authority citation for these 

special conditions is as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701, 

44702, 44704. 


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Federal Register / Vol. 80, No. 83 / Thursday, April 30, 2015 / Rules and Regulations 24195 

The Special Conditions 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the following special 

conditions are issued as part of the type 

certification basis for Airbus Model 

SAneo series airplanes. 

In lieu of § 25.361(b), the following 

special conditions apply: 

1. For turbine engine installations, the 

engine mounts, pylons, and adjacent 

supporting airframe structure must be 

designed to withstand 1g level flight 

loads acting simultaneously with the 

maximum torque limit loads imposed 

by each of the following: 

a. Sudden engine deceleration due to 

a malfunction that could result in a 

temporary loss of power or thrust; and 

b. the maximum acceleration of the 

engine. 

2. For auxiliary power-unit 

installations, the power-unit mounts 

and adjacent supporting airframe 

structure must be designed to withstand 

1g level flight loads acting 

simultaneously with the maximum 

torque limit loads imposed by each of 

the following: 

a. Sudden auxiliary power-unit 

deceleration due to malfunction or 

structural failure; and 

b. the maximum acceleration of the 

power unit. 

3. For engine supporting structure, an 

ultimate loading condition must be 

considered that combines 1g flight loads 

with the transient dynamic loads 

resulting from: 

a. The loss of any fan, compressor, or 

turbine blade; and separately, 

b. where applicable to a specific 

engine design, any other engine 

structural failure that results in higher 

loads. 

4. The ultimate loads developed from 

the conditions specified in Special 

Conditions 3.a. and 3.b., above, are to be 

multiplied by a factor of 1.0 when 

applied to engine mounts and pylons; 

and multiplied by a factor of 1.25 when 

applied to adjacent supporting airframe 

structure. 

5. The airplane must be capable of 

continued safe flight considering the 

aerodynamic effects on controllability 

due to any permanent deformation that 

results from the conditions specified in 

Special Condition 3, above. 

Issued in Renton, Washington, on April 19, 

2015. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–10098 Filed 4–29–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0286; Directorate 

Identifier 2014–NM–004–AD; Amendment 

39–18145; AD 2015–08–09] 

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 737–600 

and –700 series airplanes. This AD was 

prompted by reports of cracking in the 

body station (STA) 727 bulkhead lower 

frame. This AD requires a detailed and 

open hole high frequency eddy current 

(HFEC) inspection of the left- and rightside lower frame webs and inner chords 

for cracking, and corrective actions and 

preventative modifications if necessary. 

This AD also provides for optional 

terminating action of the repetitive 

inspections, under certain conditions. 

We are issuing this AD to detect and 

correct cracking in a bulkhead lower 

frame web and inner chord, which 

could result in a severed frame and 

induced skin cracks, and could lead to 

rapid decompression of the fuselage. 

DATES: This AD is effective June 4, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 4, 2015. 

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. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0286. 

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–2014– 

0286; 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: 

Alan Pohl, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6450; fax: 

425–917–6590; email: alan.pohl@

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 737–600 and –700 series 

airplanes. The NPRM published in the 

Federal Register on May 28, 2014 (79 

FR 30490). The NPRM was prompted by 

reports of cracking in the body STA 727 

bulkhead lower frame. The NPRM 

proposed to require a detailed and open 

hole high frequency eddy current 

(HFEC) inspection of the left- and rightside lower frame webs and inner chords 

for cracking, as applicable, and 

corrective actions and preventative 

modifications if necessary. The NPRM 

also proposed to provide for an optional 

terminating action for the repetitive 

inspections under certain conditions. 

We are issuing this AD to detect and 

correct cracking in a bulkhead lower 

frame web and inner chord, which 

could result in a severed frame and 

induced skin cracks, and could lead to 

rapid decompression of the fuselage. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. 

Boeing and United Airlines stated that 

they support the NPRM (79 FR 30490, 

May 28, 2014). The following presents 

the comments received on the NPRM, 

and the FAA’s response to each 

comment. 

Request To Clarify Modification and 

Repair Requirements 

Southwest Airlines (SWA) requested 

that we clarify whether the preventative 

modifications and repairs of the lower 

frame webs and inner chords (if 


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