80 FR 34242 - Special Conditions: Honda Aircraft Company, Model HA-420; Fire Extinguishing for Overwing Pylon Mounted Engines
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 115 (June 16, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 115 (June 16, 2015)
| Page Range | 34242-34244 | |
| FR Document | 2015-14816 |
[Federal Register Volume 80, Number 115 (Tuesday, June 16, 2015)] [Rules and Regulations] [Pages 34242-34244] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-14816] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 23 [Docket No. FAA-2015-0722; Special Conditions No. 23-265-SC] Special Conditions: Honda Aircraft Company, Model HA-420; Fire Extinguishing for Overwing Pylon Mounted Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final special conditions; request for comments. ----------------------------------------------------------------------- SUMMARY: These special conditions are issued for the Honda Aircraft Company model HA-420 airplane. This airplane will have a novel or unusual design feature associated with mounting the engines on the wings in close proximity to the aft fuselage. 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 June 16, 2015. We must receive your comments by July 16, 2015. ADDRESSES: Send comments identified by docket number FAA-2015-0722 using any of the following methods: [ssquf] Federal eRegulations Portal: Go to http://www.regulations.gov and follow the online instructions for sending your comments electronically. [ssquf] 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. [ssquf] Hand Delivery of 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. [ssquf] Fax: Fax comments to Docket Operations at 202-493-2251. Privacy: The FAA will post all comments it receives, without change, to http://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 the 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: Jeff Pretz, Federal Aviation Administration, Aircraft Certification Service, Small Airplane Directorate, ACE-111, 901 Locust, Kansas City, Missouri 64106; 816-329- 3239, fax 816-329-4090, email [email protected]. SUPPLEMENTARY INFORMATION: The FAA has determined, in accordance with 5 U.S.C. 553(b)(3)(B) and (d)(3), that notice and opportunity for prior public comment hereon are unnecessary because 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. ------------------------------------------------------------------------ Special condition No. Company/Airplane Model ------------------------------------------------------------------------ 23-210-SC............................. Adam Aircraft Model A700. 23-245-SC............................. Cirrus Design Corporation Model SF50. 23-221-SC............................. Embraer S.A. Model EMB-500. ------------------------------------------------------------------------ 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 ask that you send us two copies of written comments. We will consider all comments we receive on or before the closing date for comments. We will consider comments [[Page 34243]] filed late if it is possible to do so without incurring expense or delay. We may change these special conditions based on the comments we receive. Background On October 11, 2006, Honda Aircraft Company applied for a type certificate for their new model HA-420. On October 10, 2013, Honda Aircraft Company requested an extension with an effective application date of October 1, 2013. This extension changed the type certification basis to amendment 23-62. The HA-420 is a four to five passenger (depending on configuration), two crew, lightweight business jet with a 43,000-foot service ceiling and a maximum takeoff weight of 9963 pounds. The airplane is powered by two GE-Honda Aero Engines (GHAE) HF-120 turbofan engines. The turbofan engines are mounted on a single pylon on each wing near the aft fuselage. These types of aft mounted engine installations, along with the need to protect such installed engines from fires, were not envisioned in the development of the part 23 normal category regulations. The performance of the airplane is such that a pilot may not be able to locate a suitable landing site and safely land the airplane prior to a fire escaping the fire containment capabilities of the engine fire zone. Type Certification Basis Under the provisions of 14 CFR 21.17, Honda Aircraft Company must show that the model HA-420 meets the applicable provisions of part 23, as amended by Amendment 23-1 through Amendment 23-62 thereto. If the Administrator finds that the applicable airworthiness regulations (i.e., 14 CFR part 23) do not contain adequate or appropriate safety standards for the model HA-420 because of a novel or unusual design feature, special conditions are prescribed under the provisions of Sec. 21.16. In addition to the applicable airworthiness regulations and special conditions, the model HA-420 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. In addition, 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 Sec. 11.19, under Sec. 11.38 and they become part of the type certification basis under Sec. 21.17(a)(2). 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, the special conditions would also apply to the other model. Novel or Unusual Design Features The model HA-420 will incorporate the following novel or unusual design features: Turbofan engines are mounted on a single pylon on each wing near the aft fuselage not in the pilot's line of sight. This type of configuration was not envisioned in the development of part 23 normal category airplanes. Therefore, a special condition for the engine fire extinguishing system on the model HA-420 is required. As the extinguishing agent is subject to change during the service life of the airplane, the certification basis must include SC 23.1195, SC 23.1197, SC 23.1199, and SC 23.1201 in their entirety. Discussion Part 23 has historically addressed fire protection through prevention, identification, and containment. Prevention has been accomplished by minimizing the potential for ignition of flammable fluids and vapors. Identification has traditionally been achieved by the location of the engines within the pilot's primary field of view and/or with the incorporation of fire detection systems. This philosophy has provided for both the rapid detection of a fire and confirmation when it has been extinguished. Containment has been provided through the isolation of designated fire zones through flammable fluid shutoff valves and firewalls. The containment philosophy also ensures components of the engine control system will function effectively to permit a safe shutdown of the engine. However, containment has only been required to be demonstrated for 15 minutes. In the event of a fire in a traditional part 23 airplane, the corrective action is to land as soon as possible. For a small, simple aircraft originally envisioned by part 23, it is possible to descend the aircraft to a suitable landing site within 15 minutes. Thus, if the isolation means do not extinguish the fire, the occupants can safely exit the aircraft prior to breaching the firewall. These simple and traditional aircraft normally have the engine located away from critical flight control systems and primary structure. This has ensured that throughout the fire event the pilot can maintain control and continue safe flight. It has also made predicting the effects of a fire relatively easy. Other design features of these simple and traditional aircraft, such as low stall speeds and short landing distances, ensure that even in the event of an off field landing the potential for a catastrophic outcome has been minimized. Amendment 23-62 applies to the model HA-420 and addresses the concerns above by requiring engine fire extinguishing for engines embedded in the fuselage or in pylons on the aft fuselage, but do not address engines mounted in pylons over the wing as used on the model HA-420. The engine fire concerns for engines mounted in overwing pylons near the aft fuselage are the same as those associated with engines mounted in pylons on the aft fuselage; therefore, the engine fire extinguishing requirements included in part 23, amendments 23-1 through 23-62 apply. Applicability As discussed above, these special conditions are applicable to the model HA-420. Should Honda Airplane Company 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 of airplanes. It is not a rule of general applicability and affects only the applicant who applied to the FAA for approval of these features on the airplane. The substance of these special conditions has been subjected to the notice and comment period in several prior instances, identified above, and has been derived without substantive change from those previously issued. It is unlikely that prior public comment would result in a significant change from the substance contained herein. Therefore, notice and opportunity for prior public comment hereon are unnecessary and the FAA finds good cause, in accordance with 5 U.S.C. 553(b)(3)(B) and (d)(3), making these special conditions effective upon issuance. 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 23 Aircraft, Aviation safety, Signs and symbols. [[Page 34244]] Citation The authority citation for these special conditions is as follows: Authority: 49 U.S.C. 106(g), 40113 and 44701; 14 CFR 21.16 and 21.17; and 14 CFR 11.38 and 11.19. The Special Conditions 0 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 Honda Airplane Company model HA-420 airplanes. 1. Fire Extinguishing for Overwing Pylon Mounted Engines SC 23.1195 Fire Extinguishing Systems (a) Fire extinguishing systems must be installed and compliance shown with the following: (1) Except for combustor, turbine, and tailpipe sections of turbine-engine installations that contain lines or components carrying flammable fluids or gases for which a fire originating in these sections is shown to be controllable, a fire extinguisher system must serve each engine compartment. (2) The fire extinguishing system, the quantity of the extinguishing agent, the rate of discharge, and the discharge distribution must be adequate to extinguish fires. An individual ``one- shot'' system may be used except for embedded engines where a ``two shot'' system must be used. (3) The fire extinguishing system for a nacelle must be able to simultaneously protect each compartment of the nacelle for which protection is provided. (b) If an auxiliary power unit is installed in any airplane certificated to this part, that auxiliary power unit compartment must be served by a fire extinguishing system meeting the requirements of paragraph (a)(2) of this section. SC 23.1197 Fire Extinguishing Agents The following applies: (a) Fire extinguishing agents must-- (1) Be capable of extinguishing flames emanating from any burning of fluids or other combustible materials in the area protected by the fire extinguishing system; and (2) Have thermal stability over the temperature range likely to be experienced in the compartment in which they are stored. (b) If any toxic extinguishing agent is used, provisions must be made to prevent harmful concentrations of fluid or fluid vapors (from leakage during normal operation of the airplane or as a result of discharging the fire extinguisher on the ground or in flight) from entering any personnel compartment, even though a defect may exist in the extinguishing system. This must be shown by test except for built- in carbon dioxide fuselage compartment fire extinguishing systems for which-- (1) Five pounds or less of carbon dioxide will be discharged, under established fire control procedures, into any fuselage compartment; or (2) Protective breathing equipment is available for each flight member on flight deck duty. SC 23.1199 Extinguishing Agent Containers The following applies: (a) Each extinguishing agent container must have a pressure relief valve to prevent bursting of the container by excessive internal pressures. (b) The discharge end of each discharge line from a pressure relief connection must be located so that discharge of the fire-extinguishing agent would not damage the airplane. The line must also be located or protected to prevent clogging caused by ice or other foreign matter. (c) A means must be provided for each fire extinguishing agent container to indicate that the container has discharged or that the charging pressure is below the established minimum necessary for proper functioning. (d) The temperature of each container must be maintained under intended operating conditions, to prevent the pressure in the container from-- (1) Falling below that necessary to provide an adequate rate of discharge; or (2) Rising high enough to cause premature discharge. (e) If a pyrotechnic capsule is used to discharge the extinguishing agent, each container must be installed so that temperature conditions will not cause hazardous deterioration of the pyrotechnic capsule. SC 23.1201 Fire Extinguishing System Materials The following apply: (a) No material in any fire extinguishing system may react chemically with any extinguishing agent so as to create a hazard. (b) Each system component in an engine compartment must be fireproof. Issued in Kansas City, Missouri, on June 9, 2015. Earl Lawrence, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-14816 Filed 6-15-15; 8:45 am] BILLING CODE 4910-13-P
![34242 Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Rules and Regulations
no extraordinary circumstances creating § 293.4 [Removed] Privacy: The FAA will post all
the potential for significant ■ 5. Remove § 293.4. comments it receives, without change,
environmental effects. Therefore, this to http://regulations.gov, including any
rule is categorically excluded from Jeh Charles Johnson, personal information the commenter
further NEPA review. Secretary of Homeland Security. provides. Using the search function of
[FR Doc. 2015–14675 Filed 6–15–15; 8:45 am] the docket Web site, anyone can find
List of Subjects in 8 CFR Part 293 and read the electronic form of all
BILLING CODE 9111–28–P
Administrative practice and comments received into any FAA
procedure, Aliens, Bonds, Immigration, docket, including the name of the
Interest rate. DEPARTMENT OF TRANSPORTATION individual sending the comment (or
signing the comment for an association,
Amendments to the Regulations business, labor union, etc.). DOT’s
Federal Aviation Administration
For the reasons discussed in the complete Privacy Act Statement can be
preamble, DHS amends 8 CFR part 293 14 CFR Part 23 found in the Federal Register published
as follows: on April 11, 2000 (65 FR 19477–19478),
[Docket No. FAA–2015–0722; Special as well as at http://DocketsInfo.dot.gov.
PART 293—DEPOSIT OF AND Conditions No. 23–265–SC] Docket: Background documents or
INTEREST ON CASH RECEIVED TO comments received may be read at
Special Conditions: Honda Aircraft
SECURE IMMIGRATION BONDS http://www.regulations.gov at any time.
Company, Model HA–420; Fire
Follow the online instructions for
1. Revise the authority citation for part Extinguishing for Overwing Pylon
■ accessing the docket or go to the Docket
293 to read as follows: Mounted Engines Operations in Room W12–140 of the
Authority: 8 U.S.C. 1363. AGENCY: Federal Aviation West Building Ground Floor at 1200
Administration (FAA), DOT. New Jersey Avenue SE., Washington,
■ 2. Revise § 293.1 to read as follows: DC, between 9 a.m., and 5 p.m., Monday
ACTION: Final special conditions; request
for comments. through Friday, except Federal holidays.
§ 293.1 Computation of interest. FOR FURTHER INFORMATION CONTACT: Jeff
The Secretary of the Treasury SUMMARY: These special conditions are Pretz, Federal Aviation Administration,
determines the rate at which an issued for the Honda Aircraft Company Aircraft Certification Service, Small
immigration bond secured by cash shall model HA–420 airplane. This airplane Airplane Directorate, ACE–111, 901
bear interest, consistent with 8 CFR will have a novel or unusual design Locust, Kansas City, Missouri 64106;
293.2. Interest shall be computed from feature associated with mounting the 816–329–3239, fax 816–329–4090, email
the deposit date to and including the engines on the wings in close proximity jeff.pretz@faa.gov.
refund date or breach date of the to the aft fuselage. The applicable SUPPLEMENTARY INFORMATION: The FAA
immigration bond. For purposes of this airworthiness regulations do not contain has determined, in accordance with 5
part, the deposit date shall be the date adequate or appropriate safety standards U.S.C. 553(b)(3)(B) and (d)(3), that
shown on the receipt for the cash for this design feature. These special notice and opportunity for prior public
received as security on an immigration conditions contain the additional safety comment hereon are unnecessary
bond. The refund date shall be the date standards that the Administrator because the substance of these special
upon which the interest is certified to considers necessary to establish a level conditions has been subject to the
the Treasury Department for payment. of safety equivalent to that established public comment process in several prior
The breach date shall be the date the by the existing airworthiness standards. instances with no substantive comments
immigration bond was breached as DATES: The effective date of these received. The FAA therefore finds that
shown on Form I–323—‘‘Notice— special conditions is June 16, 2015. good cause exists for making these
Immigration Bond Breached.’’ In We must receive your comments by special conditions effective upon
counting the number of days for which July 16, 2015. issuance.
interest shall be computed, the day on ADDRESSES: Send comments identified
which the cash was deposited shall not by docket number FAA–2015–0722 Special condition Company/Airplane Model
be counted; however, the refund date or No.
using any of the following methods:
the breach date shall be counted. D Federal eRegulations Portal: Go to 23–210–SC ....... Adam Aircraft Model A700.
■ 3. Revise § 293.2 to read as follows: http://www.regulations.gov and follow 23–245–SC ....... Cirrus Design Corporation
the online instructions for sending your Model SF50.
§ 293.2 Interest rate. 23–221–SC ....... Embraer S.A. Model EMB–
comments electronically.
Interest on cash deposited to secure D Mail: Send comments to Docket 500.
immigration bonds will be at the rate as Operations, M–30, U.S. Department of
determined by the Secretary of the Transportation (DOT), 1200 New Jersey Comments Invited
Treasury, but in no case will exceed 3 Avenue SE., Room W12–140, West We invite interested people to take
per centum per annum or be less than Building Ground Floor, Washington, part in this rulemaking by sending
zero. The rate will be published by DC, 20590–0001. written comments, data, or views. The
Treasury on the Treasury Web site or D Hand Delivery of Courier: Take most helpful comments reference a
asabaliauskas on DSK5VPTVN1PROD with RULES
through another mechanism. comments to Docket Operations in specific portion of the special
■ 4. Revise § 293.3 to read as follows: Room W12–140 of the West Building conditions, explain the reason for any
Ground Floor at 1200 New Jersey recommended change, and include
§ 293.3 Time of payment. Avenue SE., Washington, DC, between 9 supporting data. We ask that you send
Interest shall be paid only at time of a.m., and 5 p.m., Monday through us two copies of written comments.
disposition of principal cash when the Friday, except Federal holidays. We will consider all comments we
immigration bond has been cancelled or D Fax: Fax comments to Docket receive on or before the closing date for
declared breached. Operations at 202–493–2251. comments. We will consider comments
VerDate Sep<11>2014 16:14 Jun 15, 2015 Jkt 235001 PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 E:\FR\FM\16JNR1.SGM 16JNR1](https://thefederalregister.org/doc/80_FR_34357/page/1.svg)
![34244 Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Rules and Regulations
Citation extinguisher on the ground or in flight) DEPARTMENT OF TRANSPORTATION
The authority citation for these from entering any personnel
compartment, even though a defect may Federal Aviation Administration
special conditions is as follows:
exist in the extinguishing system. This
Authority: 49 U.S.C. 106(g), 40113 and must be shown by test except for built- 14 CFR Part 39
44701; 14 CFR 21.16 and 21.17; and 14 CFR
in carbon dioxide fuselage compartment [Docket No. FAA–2014–0575; Directorate
11.38 and 11.19.
fire extinguishing systems for which— Identifier 2014–NM–086–AD; Amendment
The Special Conditions (1) Five pounds or less of carbon 39–18181; AD 2015–12–07]
■ Accordingly, pursuant to the authority dioxide will be discharged, under RIN 2120–AA64
delegated to me by the Administrator, established fire control procedures, into
the following special conditions are any fuselage compartment; or Airworthiness Directives; The Boeing
issued as part of the type certification (2) Protective breathing equipment is Company Airplanes
basis for Honda Airplane Company available for each flight member on
flight deck duty. AGENCY: Federal Aviation
model HA–420 airplanes. Administration (FAA), DOT.
1. Fire Extinguishing for Overwing SC 23.1199 Extinguishing Agent ACTION: Final rule.
Pylon Mounted Engines Containers
SUMMARY: We are adopting a new
SC 23.1195 Fire Extinguishing The following applies: airworthiness directive (AD) for all The
Systems (a) Each extinguishing agent container Boeing Company Model 747–8F and
must have a pressure relief valve to 747–8 series airplanes. This AD was
(a) Fire extinguishing systems must be prevent bursting of the container by
installed and compliance shown with prompted by reports of delamination
excessive internal pressures. damage to leading edge (LE) variable
the following:
(b) The discharge end of each camber krueger (VCK) flaps. This AD
(1) Except for combustor, turbine, and
discharge line from a pressure relief requires repetitive inspections to detect
tailpipe sections of turbine-engine
connection must be located so that delamination damage of the lightning
installations that contain lines or
discharge of the fire-extinguishing agent strike applique (LSA) on certain LE VCK
components carrying flammable fluids
would not damage the airplane. The line flaps, and corrective actions if
or gases for which a fire originating in
must also be located or protected to necessary. We are issuing this AD to
these sections is shown to be
prevent clogging caused by ice or other detect and correct delamination damage
controllable, a fire extinguisher system
foreign matter. to certain LE VCK flaps, which can
must serve each engine compartment.
(2) The fire extinguishing system, the (c) A means must be provided for reduce the lightning strike protection
quantity of the extinguishing agent, the each fire extinguishing agent container capability on certain LE VCK flaps and
rate of discharge, and the discharge to indicate that the container has result in an uncommanded motion of
distribution must be adequate to discharged or that the charging pressure the trailing edge flap system; such
extinguish fires. An individual ‘‘one- is below the established minimum uncommanded flap motion, without
shot’’ system may be used except for necessary for proper functioning. shutdown of the trailing edge or leading
embedded engines where a ‘‘two shot’’ (d) The temperature of each container edge flaps, could cause unexpected
system must be used. must be maintained under intended changes in lift, potentially resulting in
(3) The fire extinguishing system for operating conditions, to prevent the asymmetric lift and loss of control of the
a nacelle must be able to simultaneously pressure in the container from— airplane.
protect each compartment of the nacelle (1) Falling below that necessary to DATES: This AD is effective July 21,
for which protection is provided. provide an adequate rate of discharge; or 2015.
(b) If an auxiliary power unit is (2) Rising high enough to cause The Director of the Federal Register
installed in any airplane certificated to premature discharge. approved the incorporation by reference
this part, that auxiliary power unit (e) If a pyrotechnic capsule is used to of a certain publication listed in this AD
compartment must be served by a fire discharge the extinguishing agent, each as of July 21, 2015.
extinguishing system meeting the container must be installed so that ADDRESSES: For service information
requirements of paragraph (a)(2) of this temperature conditions will not cause identified in this AD, contact Boeing
section. hazardous deterioration of the Commercial Airplanes, Attention: Data
pyrotechnic capsule. & Services Management, P. O. Box 3707,
SC 23.1197 Fire Extinguishing Agents MC 2H–65, Seattle, WA 98124–2207;
The following applies: SC 23.1201 Fire Extinguishing System telephone 206–544–5000, extension 1;
(a) Fire extinguishing agents must— Materials fax 206–766–5680; Internet https://
(1) Be capable of extinguishing flames The following apply: www.myboeingfleet.com. You may view
emanating from any burning of fluids or (a) No material in any fire this referenced service information at
other combustible materials in the area extinguishing system may react the FAA, Transport Airplane
protected by the fire extinguishing chemically with any extinguishing agent Directorate, 1601 Lind Avenue SW.,
system; and so as to create a hazard. Renton, WA. For information on the
(2) Have thermal stability over the (b) Each system component in an availability of this material at the FAA,
temperature range likely to be engine compartment must be fireproof. call 425–227–1221. It is also available
asabaliauskas on DSK5VPTVN1PROD with RULES
experienced in the compartment in on the Internet at http://
which they are stored. Issued in Kansas City, Missouri, on June 9, www.regulations.gov by searching for
(b) If any toxic extinguishing agent is 2015.
and locating Docket No. FAA 2014–
used, provisions must be made to Earl Lawrence, 0575.
prevent harmful concentrations of fluid Small Airplane Directorate, Aircraft
or fluid vapors (from leakage during Certification Service. Examining the AD Docket
normal operation of the airplane or as a [FR Doc. 2015–14816 Filed 6–15–15; 8:45 am] You may examine the AD docket on
result of discharging the fire BILLING CODE 4910–13–P the Internet at http://
VerDate Sep<11>2014 16:14 Jun 15, 2015 Jkt 235001 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 E:\FR\FM\16JNR1.SGM 16JNR1](https://thefederalregister.org/doc/80_FR_34357/page/3.svg)
Document Created: 2018-02-22 10:23:02
Document Modified: 2018-02-22 10:23:02
| 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 | The effective date of these special conditions is June 16, 2015. | |
| Contact | Jeff Pretz, Federal Aviation Administration, Aircraft Certification Service, Small Airplane Directorate, ACE-111, 901 Locust, Kansas City, Missouri 64106; 816-329- 3239, fax 816-329-4090, email [email protected] | |
| FR Citation | 80 FR 34242 | |
| CFR Associated | Aircraft; Aviation Safety and Signs and Symbols |
2025 Federal Register | Disclaimer | Privacy Policy
USC | CFR | eCFR