80_FR_55406 80 FR 55228 - Special Conditions: Gulfstream Aerospace Corporation Model GVII-G500 Airplanes; Limit Engine Torque Loads

80 FR 55228 - Special Conditions: Gulfstream Aerospace Corporation Model GVII-G500 Airplanes; Limit Engine Torque Loads

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 178 (September 15, 2015)

Page Range55228-55229
FR Document2015-23100

These special conditions are issued for the Gulfstream Model GVII-G500 airplane. These airplanes have a novel or unusual design feature as compared to the state of technology envisioned in the airworthiness standards for transport category airplanes. This design feature includes engine size and the potential torque loads imposed by sudden engine stoppage. 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.

Federal Register, Volume 80 Issue 178 (Tuesday, September 15, 2015) 
[Federal Register Volume 80, Number 178 (Tuesday, September 15, 2015)]
[Rules and Regulations]
[Pages 55228-55229]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2015-23100]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 25

[Docket No. FAA-2015-1483; Special Conditions No. 25-598-SC]


Special Conditions: Gulfstream Aerospace Corporation Model GVII-
G500 Airplanes; Limit Engine Torque Loads

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions; request for comments.

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SUMMARY: These special conditions are issued for the Gulfstream Model 
GVII-G500 airplane. These airplanes have a novel or unusual design 
feature as compared to the state of technology envisioned in the 
airworthiness standards for transport category airplanes. This design 
feature includes engine size and the potential torque loads imposed by 
sudden engine stoppage. 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: The effective date of these special conditions is September 15, 
2015. We must receive your comments by October 30, 2015.

ADDRESSES: Send comments identified by docket number FAA-2015-1483 
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: Walt Sippel, FAA, Airframe and Cabin 
Safety Branch, ANM-115, Transport Airplane Directorate, Aircraft 
Certification Service, 1601 Lind Avenue SW., Renton, Washington 98057-
3356; telephone 425-227-2774; facsimile 425-227-1232.

SUPPLEMENTARY INFORMATION: The FAA has determined that notice of, and 
opportunity for, prior public comment on these special conditions are 
impracticable because these procedures would significantly delay 
issuance of the design approval and thus delivery of the affected 
airplane.
    In addition, 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 
issuance.

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 on or before the closing 
date for comments. We may change these special conditions based on the 
comments we receive.

Background

    On March 29, 2012, Gulfstream Aerospace Corporation applied for a 
type certificate for their new Model GVII-G500 airplane.
    The GVII airplane is a large-cabin business jet with seating for 19 
passengers. It incorporates a low, swept-wing design with winglets and 
a T-tail. The Model GVII-G500 airplane is powered by two aft-fuselage-
mounted Pratt & Whitney turbofan engines. Avionics will include four 
primary display units and multiple touchscreen controllers. The flight-
control system is a three-axis fly-by-wire system controlled by active 
control/coupled side sticks.
    The Model GVII-G500 airplane wingspan is approximately 87 ft with a 
length of just over 91 ft. Maximum takeoff weight will be approximately 
76,850 lbs and maximum takeoff thrust will be approximately 15,135 lbs. 
Maximum range will be approximately 5,000 nm and maximum operating 
altitude will be 51,000 ft.

Type Certification Basis

    Under the provisions of Title 14, Code of Federal Regulations (14 
CFR) 21.17, Gulfstream Aerospace Corporation must show that the Model 
GVII-500 airplane meets the applicable provisions of part 25, as 
amended by Amendments 25-1 through 25-137 thereto.
    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 GVII-G500 airplane because 
of a novel or unusual design feature, special conditions are prescribed 
under the provisions of 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 or similar 
novel or unusual design feature, the special conditions would also 
apply to the other model under Sec.  21.101.
    In addition to the applicable airworthiness regulations and special 
conditions, the Model GVII-G500 airplane 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, in 
accordance with Sec.  11.38, and they become part of

[[Page 55229]]

the type-certification basis under Sec.  21.17(a)(2).

Novel or Unusual Design Features

    The Model GVII-G500 airplane will incorporate the following novel 
or unusual design features: Large-bypass engines capable of larger and 
more complex dynamic loads than were envisioned when the 14 CFR 
25.361(b) rule was developed in 1957, thereby requiring issuance of 
special conditions to establish appropriate design standards for the 
Model GVII-G500 airplane.

Discussion

    The limit engine torque load imposed by sudden engine stoppage due 
to malfunction or structural failure (such as a compressor jamming) has 
been a specific requirement for transport-category airplanes since 
1957. In the past, the design torque loads associated with typical 
failure scenarios have been estimated by the engine manufacturer and 
were provided to the airframe manufacturer as limit loads. These limit 
loads were considered simple, pure-torque static loads.
    It is evident from service history 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 distinguish between the more 
common engine-failure events and those rare events resulting from 
structural failures. The more-common events are regarded 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) are regarded as full dynamic load conditions. These are 
considered ultimate loads, and include all transient loads associated 
with the event. An additional safety factor is applied to the more-
critical airframe supporting structure.

Applicability

    As discussed above, these special conditions are applicable to the 
Model GVII-G500 airplane. Should Gulfstream Aerospace apply at a later 
date 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 one model series of airplane. 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 the Gulfstream Aerospace Corporation 
Model GVII-G500 airplane.
    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 limit torque 
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 (APU) installations, the power unit 
mounts and adjacent supporting airframe structure must be designed to 
withstand 1g level-flight loads acting simultaneously with the maximum 
limit torque loads imposed by each of the following:
    a. Sudden APU deceleration due to malfunction or structural 
failure; and
    b. The maximum acceleration of the APU.
    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. Any permanent deformation that results from the conditions 
specified in special condition 3, above, must not prevent continued 
safe flight and landing.

    Issued in Renton, Washington, on September 1, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-23100 Filed 9-14-15; 8:45 am]
 BILLING CODE 4910-13-P

55228 Federal Register / Vol. 80, No. 178 / Tuesday, September 15, 2015 / Rules and Regulations Issued in Renton, Washington, on a.m. and 5 p.m., Monday through conditions based on the comments we September 9, 2015. Friday, except Federal holidays. receive. Michael Kaszycki, • Fax: Fax comments to Docket Background Acting Manager, Transport Airplane Operations at 202–493–2251. Directorate, Aircraft Certification Service. Privacy: The FAA will post all On March 29, 2012, Gulfstream [FR Doc. 2015–23099 Filed 9–14–15; 8:45 am] comments it receives, without change, Aerospace Corporation applied for a BILLING CODE 4910–13–P to http://www.regulations.gov/, type certificate for their new Model including any personal information the GVII–G500 airplane. commenter provides. Using the search The GVII airplane is a large-cabin DEPARTMENT OF TRANSPORTATION function of the docket Web site, anyone business jet with seating for 19 can find and read the electronic form of passengers. It incorporates a low, swept- Federal Aviation Administration all comments received into any FAA wing design with winglets and a T-tail. docket, including the name of the The Model GVII–G500 airplane is 14 CFR Part 25 individual sending the comment (or powered by two aft-fuselage-mounted signing the comment for an association, Pratt & Whitney turbofan engines. [Docket No. FAA–2015–1483; Special business, labor union, etc.). DOT’s Avionics will include four primary Conditions No. 25–598–SC] complete Privacy Act Statement can be display units and multiple touchscreen Special Conditions: Gulfstream found in the Federal Register published controllers. The flight-control system is Aerospace Corporation Model GVII– on April 11, 2000 (65 FR 19477–19478), a three-axis fly-by-wire system G500 Airplanes; Limit Engine Torque as well as at http://DocketsInfo.dot controlled by active control/coupled Loads .gov/. side sticks. Docket: Background documents or The Model GVII–G500 airplane AGENCY: Federal Aviation comments received may be read at wingspan is approximately 87 ft with a Administration (FAA), DOT. http://www.regulations.gov/ at any time. length of just over 91 ft. Maximum ACTION: Final special conditions; request Follow the online instructions for takeoff weight will be approximately for comments. accessing the docket or go to Docket 76,850 lbs and maximum takeoff thrust Operations in Room W12–140 of the will be approximately 15,135 lbs. SUMMARY: These special conditions are West Building Ground Floor at 1200 Maximum range will be approximately issued for the Gulfstream Model GVII– New Jersey Avenue SE., Washington, 5,000 nm and maximum operating G500 airplane. These airplanes have a DC, between 9 a.m. and 5 p.m., Monday altitude will be 51,000 ft. novel or unusual design feature as through Friday, except Federal holidays. compared to the state of technology Type Certification Basis FOR FURTHER INFORMATION CONTACT: Walt envisioned in the airworthiness Sippel, FAA, Airframe and Cabin Safety Under the provisions of Title 14, Code standards for transport category Branch, ANM–115, Transport Airplane of Federal Regulations (14 CFR) 21.17, airplanes. This design feature includes Directorate, Aircraft Certification Gulfstream Aerospace Corporation must engine size and the potential torque Service, 1601 Lind Avenue SW., show that the Model GVII–500 airplane loads imposed by sudden engine Renton, Washington 98057–3356; meets the applicable provisions of part stoppage. The applicable airworthiness telephone 425–227–2774; facsimile 25, as amended by Amendments 25–1 regulations do not contain adequate or 425–227–1232. through 25–137 thereto. appropriate safety standards for this If the Administrator finds that the SUPPLEMENTARY INFORMATION: The FAA design feature. These special conditions applicable airworthiness regulations has determined that notice of, and contain the additional safety standards (i.e., 14 CFR part 25) do not contain opportunity for, prior public comment that the Administrator considers adequate or appropriate safety standards on these special conditions are necessary to establish a level of safety for the Model GVII–G500 airplane impracticable because these procedures equivalent to that established by the because of a novel or unusual design would significantly delay issuance of existing airworthiness standards. feature, special conditions are the design approval and thus delivery of DATES: The effective date of these the affected airplane. prescribed under the provisions of special conditions is September 15, In addition, the substance of these § 21.16. 2015. We must receive your comments special conditions has been subject to Special conditions are initially by October 30, 2015. the public-comment process in several applicable to the model for which they ADDRESSES: Send comments identified prior instances with no substantive are issued. Should the type certificate by docket number FAA–2015–1483 comments received. The FAA therefore for that model be amended later to using any of the following methods: finds that good cause exists for making include any other model that • Federal eRegulations Portal: Go to these special conditions effective upon incorporates the same or similar novel http://www.regulations.gov/ and follow issuance. or unusual design feature, the special the online instructions for sending your conditions would also apply to the other comments electronically. Comments Invited model under § 21.101. • Mail: Send comments to Docket We invite interested people to take In addition to the applicable Operations, M–30, U.S. Department of part in this rulemaking by sending airworthiness regulations and special Transportation (DOT), 1200 New Jersey written comments, data, or views. The conditions, the Model GVII–G500 Avenue SE., Room W12–140, West most helpful comments reference a airplane must comply with the fuel-vent mstockstill on DSK4VPTVN1PROD with RULES Building Ground Floor, Washington, DC specific portion of the special and exhaust-emission requirements of 20590–0001. conditions, explain the reason for any 14 CFR part 34 and the noise- • Hand Delivery or Courier: Take recommended change, and include certification requirements of 14 CFR comments to Docket Operations in supporting data. part 36. Room W12–140 of the West Building We will consider all comments we The FAA issues special conditions, as Ground Floor at 1200 New Jersey receive on or before the closing date for defined in 14 CFR 11.19, in accordance Avenue SE., Washington, DC, between 9 comments. We may change these special with § 11.38, and they become part of VerDate Sep<11>2014 19:08 Sep 14, 2015 Jkt 235001 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 E:\FR\FM\15SER1.SGM 15SER1

Federal Register / Vol. 80, No. 178 / Tuesday, September 15, 2015 / Rules and Regulations 55229 the type-certification basis under Conclusion special condition 3, above, must not § 21.17(a)(2). This action affects only certain novel prevent continued safe flight and or unusual design features on one model landing. Novel or Unusual Design Features series of airplane. It is not a rule of Issued in Renton, Washington, on The Model GVII–G500 airplane will general applicability. September 1, 2015. incorporate the following novel or Michael Kaszycki, unusual design features: Large-bypass List of Subjects in 14 CFR Part 25 Acting Manager, Transport Airplane engines capable of larger and more Aircraft, Aviation safety, Reporting Directorate, Aircraft Certification Service. complex dynamic loads than were and recordkeeping requirements. [FR Doc. 2015–23100 Filed 9–14–15; 8:45 am] envisioned when the 14 CFR 25.361(b) The authority citation for these BILLING CODE 4910–13–P rule was developed in 1957, thereby special conditions is as follows: requiring issuance of special conditions Authority: 49 U.S.C. 106(g), 40113, 44701, to establish appropriate design 44702, 44704. DEPARTMENT OF TRANSPORTATION standards for the Model GVII–G500 airplane. The Special Conditions Federal Aviation Administration Accordingly, pursuant to the Discussion 14 CFR Part 39 authority delegated to me by the The limit engine torque load imposed Administrator, the following special [Docket No. FAA–2015–0926; Directorate by sudden engine stoppage due to conditions are issued as part of the type Identifier 2014–NM–121–AD; Amendment malfunction or structural failure (such certification basis for the Gulfstream 39–18263; AD 2015–18–05] as a compressor jamming) has been a Aerospace Corporation Model GVII– G500 airplane. RIN 2120–AA64 specific requirement for transport- category airplanes since 1957. In the In lieu of § 25.361(b) the following Airworthiness Directives; Airbus past, the design torque loads associated special conditions apply: 1. For turbine engine installations, the Airplanes with typical failure scenarios have been estimated by the engine manufacturer engine mounts, pylons, and adjacent AGENCY: Federal Aviation and were provided to the airframe supporting airframe structure must be Administration (FAA), Department of manufacturer as limit loads. These limit designed to withstand 1g level flight Transportation (DOT). loads were considered simple, pure- loads acting simultaneously with the ACTION: Final rule. torque static loads. maximum limit torque loads imposed by each of the following: SUMMARY: We are superseding It is evident from service history that a. Sudden engine deceleration due to Airworthiness Directive (AD) 97–07–14, the engine-failure events that tend to a malfunction that could result in a for certain Airbus Model A320–111, cause the most severe loads are fan- temporary loss of power or thrust, and –211, and –231 airplanes. AD 97–07–14 blade failures, and these events occur b. The maximum acceleration of the required modification of an area on the much less frequently than the typical engine. front spar of the wing center section by ‘‘limit’’ load condition. 2. For auxiliary power unit (APU) installing shims and new fasteners to To maintain the level of safety installations, the power unit mounts reinforce pressure floor fittings. This envisioned by § 25.361(b), more and adjacent supporting airframe new AD continues to require modifying comprehensive criteria are required for structure must be designed to withstand the rib flange on the front spar of the the new generation of high-bypass 1g level-flight loads acting wing center section by installing shims engines. These special conditions simultaneously with the maximum limit and new fasteners to reinforce pressure distinguish between the more common torque loads imposed by each of the floor fittings; and requires repetitive engine-failure events and those rare following: high frequency eddy current inspections events resulting from structural failures. a. Sudden APU deceleration due to for cracking of the radius of the rib The more-common events are regarded malfunction or structural failure; and flanges and vertical stiffener at frame 36, as static torque limit load conditions. b. The maximum acceleration of the a rototest inspection for cracking of the The more-severe events resulting from APU. fastener holes of the rib flanges, repair 3. For engine supporting structure, an extreme engine-failure conditions (such if needed, and adding additional ultimate loading condition must be as loss of a full fan blade at redline airplanes to the applicability. This AD considered that combines 1g flight loads speed) are regarded as full dynamic load was prompted by the need for repetitive with the transient dynamic loads conditions. These are considered inspections on airplanes on which the resulting from: ultimate loads, and include all transient a. The loss of any fan, compressor, or modification of the rib flange on the loads associated with the event. An turbine blade; and separately, front spar of the wing center section has additional safety factor is applied to the b. Where applicable to a specific been done. We are issuing this AD to more-critical airframe supporting engine design, any other engine prevent fatigue cracking on the rib structure. structural failure that results in higher flange area of the front spar of the wing Applicability loads. center section, which can reduce the 4. The ultimate loads developed from structural integrity of fuselage frame 36 As discussed above, these special the conditions specified in special and the wing center section. conditions are applicable to the Model conditions 3(a) and 3(b), above, are to be DATES: This AD becomes effective mstockstill on DSK4VPTVN1PROD with RULES GVII–G500 airplane. Should Gulfstream multiplied by a factor of 1.0 when October 20, 2015. Aerospace apply at a later date for a applied to engine mounts and pylons, The Director of the Federal Register change to the type certificate to include and multiplied by a factor of 1.25 when approved the incorporation by reference another model incorporating the same applied to adjacent supporting airframe of a certain publication listed in this AD novel or unusual design feature, the structure. as of October 20, 2015. special conditions would apply to that 5. Any permanent deformation that The Director of the Federal Register model as well. results from the conditions specified in approved the incorporation by reference VerDate Sep<11>2014 19:08 Sep 14, 2015 Jkt 235001 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 E:\FR\FM\15SER1.SGM 15SER1


Document Created: 2015-12-15 10:09:30
Document Modified: 2015-12-15 10:09:30
CategoryRegulatory Information
CollectionFederal Register
sudoc ClassAE 2.7:
GS 4.107:
AE 2.106:
PublisherOffice of the Federal Register, National Archives and Records Administration
SectionRules and Regulations
ActionFinal special conditions; request for comments.
DatesThe effective date of these special conditions is September 15, 2015. We must receive your comments by October 30, 2015.
ContactWalt Sippel, FAA, Airframe and Cabin Safety Branch, ANM-115, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue SW., Renton, Washington 98057- 3356; telephone 425-227-2774; facsimile 425-227-1232.
FR Citation80 FR 55228 
CFR AssociatedAircraft; Aviation Safety and Reporting and Recordkeeping Requirements
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