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Federal Register / Vol. 86, No. 189 / Monday, October 4, 2021 / Rules and Regulations
Applicability As discussed above, these special conditions are applicable to the Boeing Model 7779 series airplane. Should Boeing apply at a later date 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 a certain novel or unusual design feature on one model series of airplanes. It is not a rule of general applicability.
List of Subjects in 14 CFR Part 25
Aircraft, Aviation safety, Reporting and recordkeeping requirements.
Authority Citation The authority citation for these special conditions is as follows:
Authority: 49 U.S.C. 106f, 106g, 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 Boeing Commercial Airplanes Model 7779
series airplanes.
In lieu of 14 CFR 25.1351d, the following special conditions apply:
a The applicant must show by test or a combination of test and analysis that the airplane is capable of continued safe flight and landing with all normal electrical power sources inoperative, as prescribed by paragraphs a1 and a2, below. For purposes of these special conditions, normal sources of electrical power generation do not include any alternate power sources such as the battery, ram air turbine, or independent power systems such as the flight control permanent magnet generating system. In showing capability for continued safe flight and landing, the applicant must account for systems capability, effects on crew workload and operating conditions, and the physiological needs of the flightcrew and passengers for the longest diversion time for which the applicant is seeking approval.
1 In showing compliance with this requirement, the applicant must account for common-cause failures, cascading failures, and zonal physical threats.
2 The applicant may consider the ability to restore operation of portions of the electrical power generation and distribution system if it can be shown that unrecoverable loss of those portions
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of the system is extremely improbable.
The design must provide an alternative source of electrical power for the time required to restore the minimum electrical power generation capability required for safe flight and landing. The applicant may exclude unrecoverable loss of all engines when showing compliance with this requirement.
b Regardless of any electrical generation and distribution system recovery capability shown under paragraph a of these special conditions, sufficient electrical system capability must be provided to:
1 Allow time to descend, with all engines inoperative, at the speed that provides the best glide distance, from the maximum operating altitude to the top of the engine restart envelope, and 2 Subsequently allow multiple start attempts of the engines and auxiliary power unit APU. The design must provide this capability in addition to the electrical capability required by existing part 25 requirements related to operation with all engines inoperative.
c The airplane emergency electrical power system must be designed to supply:
1 Electrical power required for immediate safety, which must continue to operate without the need for crew action following the loss of the normal electrical power, for a duration sufficient to allow reconfiguration to provide a non-time-limited source of electrical power.
2 Electrical power required for continued safe flight and landing for the maximum diversion time.
d If the applicant uses APUgenerated electrical power to satisfy the requirements of these special conditions, and if reaching a suitable runway for landing is beyond the capacity of the battery systems, then the APU must be able to be started under any foreseeable flight condition prior to the depletion of the battery or the restoration of normal electrical power, whichever occurs first. Flight test must demonstrate this capability at the most critical condition.
1 The applicant must show that the APU will provide adequate electrical power for continued safe flight and landing.
2 The operating limitations section of the airplane flight manual AFM
must incorporate non-normal procedures that direct the pilot to take appropriate actions to activate the APU
after loss of normal engine-driven generated electrical power.
e As part of showing compliance with these special conditions, the tests to demonstrate loss of all normal
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electrical power must also take into account the following:
1 The assumption that the failure condition occurs during night instrument meteorological conditions IMC at the most critical phase of the flight, relative to the worst possible electrical power distribution and equipment-loads-demand condition.
2 After the un-restorable loss of normal engine generator power, the airplane engine restart capability is provided and operations continued in IMC.
3 The airplane is demonstrated to be capable of continued safe flight and landing. The length of time must be computed based on the maximum diversion time capability for which the airplane is being certified. The applicant must account for airspeed reductions resulting from the associated failure or failures.
4 The airplane must provide adequate indication of loss of normal electrical power to direct the pilot to the non-normal procedures, and the operating limitations section of the AFM
must incorporate non-normal procedures that will direct the pilot to take appropriate actions.
Issued in Kansas City, Missouri, on September 29, 2021.
Patrick R. Mullen, Manager, Technical Innovation Policy Branch, Policy and Innovation Division, Aircraft Certification Service.
FR Doc. 202121540 Filed 10121; 8:45 am BILLING CODE 491013P

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration 14 CFR Part 71
Docket No. FAA20210648; Amendment No. 7153
RIN 2120AA66

Airspace Designations; Incorporation by Reference Amendments Federal Aviation Administration FAA, DOT.
ACTION: Final rule, administrative correction.
AGENCY:

This action incorporates certain airspace designation amendments into FAA Order JO
7400.11F, dated August 10, 2021, and effective September 15, 2021, for incorporation by reference.
DATES: Effective date 0901 UTC October 4, 2021. The Director of the Federal Register approves this incorporation by reference action under 1 CFR part 51, SUMMARY:

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