80 FR 24193 - Special Conditions: Airbus Model A319-151n/171n, A320-251n/271n, and A321-251n/271n (SAneo) Series Airplanes; Transient Engine-Failure Loads
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 83 (April 30, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 83 (April 30, 2015)
| Page Range | 24193-24195 | |
| FR Document | 2015-10098 |
[Federal Register Volume 80, Number 83 (Thursday, April 30, 2015)] [Rules and Regulations] [Pages 24193-24195] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-10098] ----------------------------------------------------------------------- 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 transport-category 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 [[Page 24194]] 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 Sec. 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 Sec. 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 Sec. 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 Sec. 11.38, and they become part of the type certification basis under Sec. 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 Sec. 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 fan-blade failures, and these events occur much less frequently than the typical ``limit'' load condition. To maintain the level of safety envisioned by Sec. 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 engine-failure 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. [[Page 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 Sec. 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
![Federal Register / Vol. 80, No. 83 / Thursday, April 30, 2015 / Rules and Regulations 24193
impracticable, and good cause exists for Issued in Renton, Washington, on April 17, • Hand Delivery or Courier: Take
adopting these special conditions upon 2015. comments to Docket Operations in
publication in the Federal Register. The Victor Wicklund, Room W12–140 of the West Building
FAA is requesting comments to allow Acting Manager, Transport Airplane Ground Floor at 1200 New Jersey
interested persons to submit views that Directorate, Aircraft Certification Service. Avenue SE., Washington, DC, between 9
may not have been submitted in [FR Doc. 2015–10102 Filed 4–29–15; 8:45 am] a.m. and 5 p.m., Monday through
response to the prior opportunities for BILLING CODE 4910–13–P Friday, except Federal holidays.
comment described above. • Fax: Fax comments to Docket
List of Subjects in 14 CFR Part 25 Operations at 202–493–2251.
DEPARTMENT OF TRANSPORTATION Privacy: The FAA will post all
Aircraft, Aviation safety, Reporting comments it receives, without change,
and recordkeeping requirements. Federal Aviation Administration to http://www.regulations.gov/,
The authority citation for these including any personal information the
special conditions is as follows: 14 CFR Part 25 commenter provides. Using the search
Authority: 49 U.S.C. 106(g), 40113, 44701, function of the docket Web site, anyone
[Docket No. FAA–2014–1080; Special can find and read the electronic form of
44702, 44704. Conditions No. 25–582–SC]
all comments received into any FAA
The Special Conditions docket, including the name of the
Special Conditions: Airbus Model
Accordingly, pursuant to the A319–151n/171n, A320–251n/271n, and individual sending the comment (or
authority delegated to me by the A321–251n/271n (SAneo) Series signing the comment for an association,
Administrator, the following special Airplanes; Transient Engine-Failure business, labor union, etc.). DOT’s
conditions are issued as part of the type- Loads complete Privacy Act Statement can be
certification basis for the Bombardier found in the Federal Register published
Inc. Model BD–700–2A12 and BD–700– AGENCY: Federal Aviation on April 11, 2000 (65 FR 19477–19478),
2A13 airplanes. Administration (FAA), DOT. as well as at
ACTION: Final special conditions; request http://DocketsInfo.dot.gov/.
Design Roll Maneuver Condition
for comments. Docket: Background documents or
In lieu of compliance to § 25.349(a): comments received may be read at
The following conditions, speeds, and SUMMARY: These special conditions are http://www.regulations.gov/ at any time.
cockpit roll-control motions (except as issued for Airbus Model A319–151n/ Follow the online instructions for
the motions may be limited by pilot 171n, A320–251n/271n, and A321– accessing the docket or go to Docket
effort) must be considered in 251n/271n (collectively known as Operations in Room W12–140 of the
combination with an airplane load Single Aisle new engine option (SA West Building Ground Floor at 1200
factor of zero and of two-thirds of the neo)) series airplanes. These airplanes New Jersey Avenue SE., Washington,
positive maneuvering factor used in will have a novel or unusual design DC, between 9 a.m. and 5 p.m., Monday
design. In determining the resulting feature when compared to the state of through Friday, except Federal holidays.
control-surface deflections, the torsional technology envisioned in the FOR FURTHER INFORMATION CONTACT:
flexibility of the wing must be airworthiness standards for transport-
considered in accordance with Todd Martin, FAA, ANM–115,
category airplanes. This design feature Transport Airplane Directorate, Aircraft
§ 25.301(b): is a new generation of high-bypass
1. Bombardier Inc. must investigate Certification Service, 1601 Lind Avenue
engines, and the potential loads SW., Renton, Washington 98057–3356;
conditions corresponding to steady resulting from extreme engine-failure
rolling velocities. In addition, telephone 425–227–1178; facsimile
conditions. 425–227–1320.
conditions corresponding to maximum The applicable airworthiness
angular acceleration must be SUPPLEMENTARY INFORMATION: The FAA
regulations do not contain adequate or
investigated for airplanes with engines has determined that notice of, and
appropriate safety standards for this
or other weight concentrations outboard opportunity for prior public comment
design feature. These special conditions
of the fuselage. For the angular on, these special conditions is
contain the additional safety standards
acceleration conditions, zero rolling unnecessary.
that the Administrator considers
velocity may be assumed in the absence The substance of these special
necessary to establish a level of safety
of a rational time-history investigation conditions has been subject to the
equivalent to that established by the
of the maneuver. public comment process in several prior
existing airworthiness standards.
2. At VA, sudden movement of the instances with no substantive comments
cockpit roll control up to the limit is DATES: This action is effective on Airbus received. The FAA therefore finds that
assumed. The position of the cockpit on April 30, 2015. We must receive your good cause exists for making these
roll control must be maintained until a comments by June 15, 2015. special conditions effective upon
steady roll rate is achieved and then ADDRESSES: Send comments identified publication in the Federal Register.
must be returned suddenly to the by docket number FAA–2014–1080
using any of the following methods: Comments Invited
neutral position.
3. At VC, the cockpit roll control must • Federal eRegulations Portal: Go to We invite interested people to take
be moved suddenly and maintained so http://www.regulations.gov/ and follow part in this rulemaking by sending
as to achieve a roll rate not less than the online instructions for sending your written comments, data, or views. The
comments electronically.
rmajette on DSK2VPTVN1PROD with RULES
that obtained in Special Condition 2, most helpful comments reference a
above. • Mail: Send comments to Docket specific portion of the special
4. At VD, the cockpit roll control must Operations, M–30, U.S. Department of conditions, explain the reason for any
be moved suddenly and maintained so Transportation (DOT), 1200 New Jersey recommended change, and include
as to achieve a roll rate not less than one Avenue SE., Room W12–140, West supporting data.
third of that obtained in Special Building Ground Floor, Washington, DC We will consider all comments we
Condition 2, above. 20590–0001. receive by the closing date for
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![Federal Register / Vol. 80, No. 83 / Thursday, April 30, 2015 / Rules and Regulations 24195
The Special Conditions DEPARTMENT OF TRANSPORTATION Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
Accordingly, pursuant to the Federal Aviation Administration except Federal holidays. The AD docket
authority delegated to me by the
contains this AD, the regulatory
Administrator, the following special 14 CFR Part 39 evaluation, any comments received, and
conditions are issued as part of the type
[Docket No. FAA–2014–0286; Directorate other information. The address for the
certification basis for Airbus Model
Identifier 2014–NM–004–AD; Amendment Docket Office (phone: 800–647–5527) is
SAneo series airplanes.
39–18145; AD 2015–08–09] Docket Management Facility, U.S.
In lieu of § 25.361(b), the following Department of Transportation, Docket
special conditions apply: RIN 2120–AA64
Operations, M–30, West Building
1. For turbine engine installations, the Ground Floor, Room W12–140, 1200
engine mounts, pylons, and adjacent Airworthiness Directives; The Boeing
Company Airplanes New Jersey Avenue SE., Washington,
supporting airframe structure must be DC 20590.
designed to withstand 1g level flight AGENCY: Federal Aviation
loads acting simultaneously with the FOR FURTHER INFORMATION CONTACT:
Administration (FAA), DOT. Alan Pohl, Aerospace Engineer,
maximum torque limit loads imposed
ACTION: Final rule. Airframe Branch, ANM–120S, FAA,
by each of the following:
a. Sudden engine deceleration due to Seattle Aircraft Certification Office,
SUMMARY: We are adopting a new
a malfunction that could result in a 1601 Lind Avenue SW., Renton, WA
airworthiness directive (AD) for certain
temporary loss of power or thrust; and 98057–3356; phone: 425–917–6450; fax:
The Boeing Company Model 737–600
425–917–6590; email: alan.pohl@
b. the maximum acceleration of the and –700 series airplanes. This AD was
faa.gov.
engine. prompted by reports of cracking in the
2. For auxiliary power-unit body station (STA) 727 bulkhead lower SUPPLEMENTARY INFORMATION:
installations, the power-unit mounts frame. This AD requires a detailed and
open hole high frequency eddy current Discussion
and adjacent supporting airframe
structure must be designed to withstand (HFEC) inspection of the left- and right- We issued a notice of proposed
1g level flight loads acting side lower frame webs and inner chords rulemaking (NPRM) to amend 14 CFR
simultaneously with the maximum for cracking, and corrective actions and part 39 by adding an AD that would
torque limit loads imposed by each of preventative modifications if necessary. apply to certain The Boeing Company
the following: This AD also provides for optional Model 737–600 and –700 series
a. Sudden auxiliary power-unit terminating action of the repetitive airplanes. The NPRM published in the
deceleration due to malfunction or inspections, under certain conditions. Federal Register on May 28, 2014 (79
structural failure; and We are issuing this AD to detect and FR 30490). The NPRM was prompted by
b. the maximum acceleration of the correct cracking in a bulkhead lower reports of cracking in the body STA 727
power unit. frame web and inner chord, which bulkhead lower frame. The NPRM
3. For engine supporting structure, an could result in a severed frame and proposed to require a detailed and open
ultimate loading condition must be induced skin cracks, and could lead to hole high frequency eddy current
considered that combines 1g flight loads rapid decompression of the fuselage. (HFEC) inspection of the left- and right-
with the transient dynamic loads DATES: This AD is effective June 4, 2015. side lower frame webs and inner chords
resulting from: The Director of the Federal Register for cracking, as applicable, and
a. The loss of any fan, compressor, or approved the incorporation by reference corrective actions and preventative
turbine blade; and separately, of a certain publication listed in this AD modifications if necessary. The NPRM
as of June 4, 2015. also proposed to provide for an optional
b. where applicable to a specific
ADDRESSES: For service information terminating action for the repetitive
engine design, any other engine
identified in this AD, contact Boeing inspections under certain conditions.
structural failure that results in higher
Commercial Airplanes, Attention: Data We are issuing this AD to detect and
loads.
& Services Management, P.O. Box 3707, correct cracking in a bulkhead lower
4. The ultimate loads developed from frame web and inner chord, which
the conditions specified in Special MC 2H–65, Seattle, WA 98124–2207;
telephone 206–544–5000, extension 1; could result in a severed frame and
Conditions 3.a. and 3.b., above, are to be induced skin cracks, and could lead to
multiplied by a factor of 1.0 when fax 206–766–5680; Internet https://
www.myboeingfleet.com. You may view rapid decompression of the fuselage.
applied to engine mounts and pylons;
and multiplied by a factor of 1.25 when this referenced service information at Comments
applied to adjacent supporting airframe the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., We gave the public the opportunity to
structure.
Renton, WA. For information on the participate in developing this AD.
5. The airplane must be capable of Boeing and United Airlines stated that
continued safe flight considering the availability of this material at the FAA,
call 425–227–1221. It is also available they support the NPRM (79 FR 30490,
aerodynamic effects on controllability May 28, 2014). The following presents
due to any permanent deformation that on the Internet at http://
www.regulations.gov by searching for the comments received on the NPRM,
results from the conditions specified in and the FAA’s response to each
Special Condition 3, above. and locating Docket No. FAA–2014–
0286. comment.
Issued in Renton, Washington, on April 19,
rmajette on DSK2VPTVN1PROD with RULES
2015. Examining the AD Docket Request To Clarify Modification and
Victor Wicklund, Repair Requirements
You may examine the AD docket on
Acting Manager, Transport Airplane the Internet at http:// Southwest Airlines (SWA) requested
Directorate, Aircraft Certification Service. www.regulations.gov by searching for that we clarify whether the preventative
[FR Doc. 2015–10098 Filed 4–29–15; 8:45 am] and locating Docket No. FAA–2014– modifications and repairs of the lower
BILLING CODE 4910–13–P 0286; or in person at the Docket frame webs and inner chords (if
VerDate Sep<11>2014 14:33 Apr 29, 2015 Jkt 235001 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 E:\FR\FM\30APR1.SGM 30APR1](https://thefederalregister.org/doc/80_FR_24276/page/3.svg)
Document Created: 2018-02-21 10:14:58
Document Modified: 2018-02-21 10:14:58
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final special conditions; request for comments. | |
| Dates | This action is effective on Airbus on April 30, 2015. We must receive your comments by June 15, 2015. | |
| 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. | |
| FR Citation | 80 FR 24193 | |
| CFR Associated | Aircraft; Aviation Safety and Reporting and Recordkeeping Requirements |
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