44658 Federal Register / Vol. 79, No. 148 / Friday, August 1, 2014 / Rules and Regulations 

engines. It features a twin-aisle, 9- 

abreast, economy-class layout, and 

accommodates side-by-side placement 

of LD–3 containers in the cargo 

compartment. The basic Airbus Model 

A350–900 airplane configuration 

accommodates 315 passengers in a 

standard two-class arrangement. The 

design cruise speed is Mach 0.85 with 

a maximum take-off weight of 602,000 

lbs. 

These special conditions for controlsurface awareness, applicable to Airbus 

Model A350–900 airplanes, require 

suitable flight-control-position 

annunciation and control-system mode 

of operation to be provided to the 

flightcrew when a flight condition exists 

in which nearly full surface authority 

(not crew-commanded) is being utilized. 

Suitability of such a display must take 

into account that some pilot-demanded 

maneuvers (e.g., rapid roll) are 

necessarily associated with intended 

full performance, which may saturate 

the surface. Therefore, simple alerting 

systems, which would function in both 

intended or unexpected control-limiting 

situations, must be properly balanced 

between needed crew awareness and 

nuisance features. A monitoring system 

that might compare airplane motion and 

surface deflection, and pilot side-stick 

controller (SSC) demand, could be 

useful for elimination of nuisance 

alerting. 

Type Certification Basis 

Under Title 14, Code of Federal 

Regulations (14 CFR) 21.17, Airbus must 

show that the Model A350–900 airplane 

meets the applicable provisions of 14 

CFR part 25, as amended by 

Amendments 25–1 through 25–129. 

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 Model A350–900 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 or similar novel 

or unusual design feature, the 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 A350–900 

airplane must comply with the fuel-vent 

and exhaust-emission requirements of 

14 CFR part 34 and the noisecertification requirements of 14 CFR 

part 36. The FAA must issue a finding 

of regulatory adequacy under section 

611 of Public Law 92–574, the ‘‘Noise 

Control Act of 1972.’’ 

The FAA issues special conditions, as 

defined in 14 CFR 11.19, under § 11.38, 

and they become part of the typecertification basis under § 21.17(a)(2). 

Novel or Unusual Design Features 

The Airbus Model A350–900 airplane 

incorporates the following novel or 

unusual design features: Electronic 

flight-control system providing controlsurface awareness and mode 

annunciation to the flightcrew. 

Discussion 

With a response-command type flightcontrol system and no direct coupling 

from cockpit controller to control 

surface, the pilot is not aware of actual 

surface position utilized to fulfill the 

requested demand. Some unusual flight 

conditions, arising from atmospheric 

conditions and/or airplane or engine 

failures, may result in full or nearly full 

surface deflection. Unless the flightcrew 

is made aware of excessive deflection or 

impending control-surface limiting, 

piloted or auto-flight system control of 

the airplane might be inadvertently 

continued in such a manner as to cause 

loss of control or other unsafe stability 

or performance characteristics. 

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. 

Discussion of Comments 

Notice of proposed special conditions 

No. 25–13–15–SC for Airbus Model 

A350–900 airplanes was published in 

the Federal Register on December 17, 

2013 (78 FR 76254). No comments were 

received, and the special conditions are 

adopted as proposed. 

Applicability 

As discussed above, these special 

conditions apply to Airbus Model 

A350–900 airplanes. Should Airbus 

apply later for a change to the type 

certificate to include another model 

incorporating the same novel or unusual 

design feature, the special conditions 

would apply to that model as well. 

Conclusion 

This action affects only certain novel 

or unusual design features on the Airbus 

Model A350–900 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. 

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 

A350–900 airplanes. 

Current airworthiness standards do 

not contain adequate safety standards 

for the design. In addition to the 

requirements of §§ 25.143, 25.671 and 

25.672, the following special conditions 

apply: 

1. The system design must ensure that 

the flightcrew is made suitably aware 

whenever the primary control means 

nears the limit of control authority. 

Note: The term ‘‘suitably aware’’ indicates 

annunciations provided to the flight crew 

that are appropriately balanced between 

nuisance and necessary crew awareness. 

2. If the design of the flight-control 

system has multiple modes of operation, 

a means must be provided to indicate to 

the crew any mode that significantly 

changes or degrades the normal 

handling or operational characteristics 

of the airplane. 

Issued in Renton, Washington, on July 11, 

2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–18175 Filed 7–31–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 25 

[Docket No. FAA–2013–0902; Special 

Conditions No. 25–521–SC] 

Special Conditions: Airbus Model 

A350–900 Series Airplane; Electronic 

Flight-Control System (EFCS) To Limit 

Pitch and Roll 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final special conditions. 

SUMMARY: These special conditions are 

issued for the Airbus Model A350–900 

airplane. This airplane will have a novel 

or unusual design feature associated 

with the electronic flight-control system 

(EFCS) that limits pitch- and rollattitude functions. The applicable 

airworthiness regulations do not contain 

adequate or appropriate safety standards 


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Federal Register / Vol. 79, No. 148 / Friday, August 1, 2014 / Rules and Regulations 44659 

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: Effective Date: September 2, 

2014. 

FOR FURTHER INFORMATION CONTACT: Joe 

Jacobsen, FAA, Airplane and Flightcrew 

Interface Branch, ANM–111, Transport 

Airplane Directorate, Aircraft 

Certification Service, 1601 Lind Avenue 

SW., Renton, Washington 98057–3356; 

telephone (425) 227–2011; facsimile 

(425) 227–1320. 

SUPPLEMENTARY INFORMATION: 

Background 

On August 25, 2008, Airbus applied 

for a type certificate for their new Model 

A350–900 airplane. Later, Airbus 

requested, and the FAA approved, an 

extension to the application for FAA 

type certification to November 15, 2009. 

The Model A350–900 airplane has a 

conventional layout with twin wingmounted Rolls-Royce Trent XWB 

engines. It features a twin-aisle, 9- 

abreast, economy-class layout, and 

accommodates side-by-side placement 

of LD–3 containers in the cargo 

compartment. The basic Model A350– 

900 airplane configuration will 

accommodate 315 passengers in a 

standard two-class arrangement. The 

design cruise speed is Mach 0.85 with 

a maximum take-off weight of 602,000 

lbs. 

A special condition to supplement 

§ 25.143 concerning pitch and roll limits 

was developed for the Airbus Model 

A320, A330, A340, and A380 airplanes 

wherein performance of the limiting 

functions was monitored throughout the 

flight-test program. The FAA expects 

similar monitoring to take place during 

the A350 flight-test program to 

substantiate the pitch- and roll-attitude 

limiting functions, and the 

appropriateness of the chosen limits. 

Type Certification Basis 

Under Title 14, Code of Federal 

Regulations (14 CFR) 21.17, Airbus must 

show that the Model A350–900 airplane 

meets the applicable provisions of 14 

CFR part 25, as amended by 

Amendments 25–1 through 25–129. 

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 Model A350–900 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 or similar novel 

or unusual design feature, the special 

conditions would also apply to the other 

model under § 21.101. 

In addition to the applicable 

airworthiness regulations and final 

special conditions, the Model A350–900 

airplane must comply with the fuel-vent 

and exhaust-emission requirements of 

14 CFR part 34, and the noisecertification requirements of 14 CFR 

part 36. The FAA must issue a finding 

of regulatory adequacy under section 

611 of Public Law 92–574, the ‘‘Noise 

Control Act of 1972.’’ 

The FAA issues special conditions, as 

defined in 14 CFR 11.19, under § 11.38, 

and they become part of the typecertification basis under § 21.17(a)(2). 

Novel or Unusual Design Features 

The Airbus Model A350–900 series 

will incorporate the following novel or 

unusual design features: an EFCS that, 

when operating in its normal mode, will 

prevent airplane pitch attitudes greater 

than +30 degrees and less than ¥15 

degrees, and roll angles greater than 

plus or minus 67 degrees. In addition, 

positive spiral stability is introduced for 

roll angles greater than 33 degrees at 

speeds below VMO/MMO. At speeds 

greater than VMO and up to VDF, 

maximum aileron-control force is 

limited to only 45 degrees maximum 

bank angle. 

Discussion 

It is expected that high thrust-toweight ratios provide the most critical 

cases for the positive-pitch limit. A 

margin in pitch control must be 

available to enable speed control in 

maneuvers such as climb after takeoff, 

and balked landing climb. The pitch 

limit must not impede likely 

maneuvering made necessary by 

collision avoidance efforts. A negativepitch limit must similarly not interfere 

with collision-avoidance capability, or 

with attaining and maintaining speeds 

near VMO/MMO for emergency descent. 

Spiral stability, which is introduced 

above 33 degrees roll angle, and the roll 

limit must not restrict attaining roll 

angles up to 66 degrees (approximately 

2.5g level turn) with flaps up and 60 

degrees (approximately 2.0g level turn) 

with flaps down. The implementation of 

this spiral stability requires a steady 

aileron-control force to maintain a 

constant bank angle above 33 degrees. 

This force must not require excessive 

pilot strength as stated in § 25.143(f). 

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. 

Discussion of Comments 

Notice of proposed special conditions 

no. 25–13–25–SC for the Airbus Model 

A350–900 airplane was published in the 

Federal Register on November 12, 2013 

(78 FR 67320). One comment supporting 

the special conditions was received. 

These special conditions are adopted as 

proposed. 

Applicability 

As discussed above, these special 

conditions apply to Airbus Model 

A350–900 airplanes. Should Airbus 

apply later for a change to the type 

certificate to include another model 

incorporating the same novel or unusual 

design feature, the special conditions 

would apply to that model as well. 

Conclusion 

This action affects only certain novel 

or unusual design features on the Airbus 

Model A350–900 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. 

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 

A350–900 airplanes. In addition to 

§ 25.143, the following requirements 

apply: 

1. The pitch-limiting function must 

not impede normal maneuvering for 

pitch angles up to the maximum 

required for normal maneuvering, 

including a normal all-enginesoperating takeoff, plus a suitable margin 

to allow for satisfactory speed control. 

2. The pitch and roll limiting 

functions must not restrict or prevent 

attaining pitch attitudes necessary for 

emergency maneuvering, or roll angles 

up to 66 degrees with flaps up or 60 

degrees with flaps down. Spiral 

stability, which is introduced above 33 

degrees roll angle, must not require 

excessive pilot strength to achieve these 

roll-limit angles. Other protections, 

which further limit the roll capability 

under certain extreme angle-of-attack, 


emcdonald on DSK67QTVN1PROD with RULES
44660 Federal Register / Vol. 79, No. 148 / Friday, August 1, 2014 / Rules and Regulations 

attitude, or high-speed conditions, are 

acceptable as long as they allow at least 

45 degrees of roll capability. 

Issued in Renton, Washington, on July 11, 

2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–18176 Filed 7–31–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0486; Directorate 

Identifier 2014–NM–126–AD; Amendment 

39–17918; AD 2014–15–16] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A319–111, –112, –115, 

–132, and –133 airplanes; Model A320– 

214, –232, and –233 airplanes; and 

Model A321–211, –231, and –232 

airplanes. This AD requires a detailed 

inspection for missing fasteners on the 

frame between certain stringers; for 

certain airplanes, a rototest inspection 

of the fastener holes for cracking; and 

corrective actions if necessary. This AD 

was prompted by a report that when the 

cabin lining was removed during a 

cabin conversion it was discovered that 

fasteners were missing on the frame. We 

are issuing this AD to detect and correct 

missing fasteners which, if not 

corrected, could affect the structural 

integrity of the airframe and could result 

in rapid decompression. 

DATES: This AD becomes effective 

August 18, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 18, 2014. 

We must receive comments on this 

AD by September 15, 2014. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC, between 9 

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

Friday, except Federal holidays. 

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.airwortheas@airbus.com; Internet http://

www.airbus.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–2014– 

0486; or in person at the Docket 

Operations office 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 street address for 

the Docket Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

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. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2014–0146, 

dated June 11, 2014 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Airbus Model A319–111, 

–112, –115, –132, and –133 airplanes; 

Model A320–214, –232, and –233 

airplanes; and Model A321–211, –231, 

and –232 airplanes. The MCAI states: 

During cabin conversion of an A320 

aeroplane, after removal of the cabin lining, 

an area was discovered where fasteners were 

missing at frame (FR) 24 between stringer 

(STR) 17 and STR18. Investigation results 

revealed that the available data concerning 

installation on the final assembly line was 

insufficient to pinpoint the exact MSN 

[manufacturer serial number] on which the 

affected assemblies were installed. However, 

a ‘group’ of MSN suspected to be affected 

was identified. Results of the static analysis 

performed show that the structure is still able 

to sustain Limit and Ultimate loads. 

However, the fatigue aspects indicate that 

long-term effects can be expected. 

This condition, if not corrected, could 

affect the structural integrity of the airframe. 

Prompted by these findings, Airbus issued 

Alert Operators Transmission (AOT) 

A53N006–14 and Service Bulletin (SB) 

A320–53–1285 to provide inspection 

instructions. 

For the reasons described above, this 

[EASA] AD requires a one-time detailed 

inspection (DET) [for missing fasteners] of 

the aeroplane structure at FR24 and, 

depending on findings, [a rototest inspection 

of the fastener holes for cracking and] 

accomplishment of applicable corrective 

actions. 

Corrective actions include repairing 

cracking and installing fasteners. 

You may examine the MCAI on the 

Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2014–0486. 

Relevant Service Information 

Airbus has issued the following 

service information. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

• Alert Operators Transmission 

A53N006–14, dated May 13, 2014. 

• Service Bulletin A320–53–1285, dated 

January 29, 2014. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of these same 

type designs. 

‘‘Contacting the Manufacturer’’ 

Paragraph in This AD 

Since late 2006, we have included a 

standard paragraph titled ‘‘Airworthy 

Product’’ in all MCAI ADs in which the 


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