Source: https://www.law.cornell.edu/cfr/text/14/appendix-A_to_part_33
Timestamp: 2017-10-21 23:26:56
Document Index: 612945900

Matched Legal Cases: ['art 33', 'art 33', 'art_33', 'art 33', 'art 33', '§ 33', '§ 43', '§ 33', 'art 33', 'arts 25', '§ 33', '§ 33']

14 CFR Appendix A to Part 33, Instructions for Continued Airworthiness | US Law | LII / Legal Information Institute
CFR › Title 14 › Chapter I › Subchapter C › Part 33 › Subpart G › Appendix A_to_part_33
14 CFR Appendix A to Part 33, Instructions for Continued Airworthiness
Appendix A to Part 33 - Instructions for Continued Airworthiness
a33.1 general
(a) This appendix specifies requirements for the preparation of Instructions for Continued Airworthiness as required by § 33.4.
(b) The Instructions for Continued Airworthiness for each engine must include the Instructions for Continued Airworthiness for all engine parts. If Instructions for Continued Airworthiness are not supplied by the engine part manufacturer for an engine part, the Instructions for Continued Airworthiness for the engine must include the information essential to the continued airworthiness of the engine.
(c) The applicant must submit to the FAA a program to show how changes to the Instructions for Continued Airworthiness made by the applicant or by the manufacturers of engine parts will be distributed.
a33.2 format
a33.3 content
(a)Engine Maintenance Manual or Section.
(1) Introduction information that includes an explanation of the engine's features and data to the extent necessary for maintenance or preventive maintenance.
(2) A detailed description of the engine and its components, systems, and installations.
(3) Installation instructions, including proper procedures for uncrating, deinhibiting, acceptance checking, lifting, and attaching accessories, with any necessary checks.
(4) Basic control and operating information describing how the engine components, systems, and installations operate, and information describing the methods of starting, running, testing, and stopping the engine and its parts including any special procedures and limitations that apply.
(5) Servicing information that covers details regarding servicing points, capacities of tanks, reservoirs, types of fluids to be used, pressures applicable to the various systems, locations of lubrication points, lubricants to be used, and equipment required for servicing.
(6) Scheduling information for each part of the engine that provides the recommended periods at which it should be cleaned, inspected, adjusted, tested, and lubricated, and the degree of inspection the applicable wear tolerances, and work recommended at these periods. However, the applicant may refer to an accessory, instrument, or equipment manufacturer as the source of this information if the applicant shows that the item has an exceptionally high degree of complexity requiring specialized maintenance techniques, test equipment, or expertise. The recommended overhaul periods and necessary cross references to the Airworthiness Limitations section of the manual must also be included. In addition, the applicant must include an inspection program that includes the frequency and extent of the inspections necessary to provide for the continued airworthiness of the engine.
(8) Information describing the order and method of removing the engine and its parts and replacing parts, with any necessary precautions to be taken. Instructions for proper ground handling, crating, and shipping must also be included.
(9) A list of the tools and equipment necessary for maintenance and directions as to their method of use.
(b)Engine Overhaul Manual or Section.
(1) Disassembly information including the order and method of disassembly for overhaul.
(4) Details of repair methods for worn or otherwise substandard parts and components along with the information necessary to determine when replacement is necessary.
(7) Instructions for storage preparation, including any storage limits.
(c)ETOPS Requirements. For an applicant seeking eligibility for an engine to be installed on an airplane approved for ETOPS, the Instructions for Continued Airworthiness must include procedures for engine condition monitoring. The engine condition monitoring procedures must be able to determine prior to flight, whether an engine is capable of providing, within approved engine operating limits, maximum continuous power or thrust, bleed air, and power extraction required for a relevant engine inoperative diversion. For an engine to be installed on a two-engine airplane approved for ETOPS, the engine condition monitoring procedures must be validated before ETOPS eligibility is granted.
A33.4 airworthiness limitations section
The Instructions for Continued Airworthiness must contain a section titled Airworthiness Limitations that is segregated and clearly distinguishable from the rest of the manual.
(a) For all engines:
(1) The Airworthiness Limitations section must set forth each mandatory replacement time, inspection interval, and related procedure required for type certification. If the Instructions for Continued Airworthiness consist of multiple documents, the section required under this paragraph must be included in the principal manual.
(2) This section must contain a legible statement in a prominent location that reads: “The Airworthiness Limitations section is FAA approved and specifies maintenance required under §§ 43.16 and 91.403 of Title 14 of the Code of Federal Regulations unless an alternative program has been FAA approved.”
(b) For rotorcraft engines having 30-second OEI and 2-minute OEI ratings:
(1) The Airworthiness Limitations section must also prescribe the mandatory post-flight inspections and maintenance actions associated with any use of either 30-second OEI or 2-minute OEI ratings.
(2) The applicant must validate the adequacy of the inspections and maintenance actions required under paragraph (b)(1) of this section A33.4.
(3) The applicant must establish an in-service engine evaluation program to ensure the continued adequacy of the instructions for mandatory post-flight inspections and maintenance actions prescribed under paragraph (b)(1) of this section A33.4 and of the data for § 33.5(b)(4) pertaining to power availability. The program must include service engine tests or equivalent service engine test experience on engines of similar design and evaluations of service usage of the 30-second OEI or 2-minute OEI ratings.
[Amdt. 33-9, 45 FR 60181, Sept. 11, 1980, as amended by Amdt. 33-13, 54 FR 34330, Aug. 18, 1989; Amdt. 33-21, 72 FR 1878, Jan. 16, 2007; Amdt. 33-25, 73 FR 48124, Aug. 18, 2008]
The following are ALL rules, proposed rules, and notices (chronologically) published in the Federal Register relating to 14 CFR Part 33 after this date.
82 FR 15611 - Special Conditions: General Electric Company, GE9X Engine Models; Incorporation of Composite Fan Blades
FR Doc. 2017-06277
Docket No. FAA-2017-0171
Special Conditions No. 33-018-SC
The effective date of these special conditions is April 14, 2017. We must receive your comments by May 1, 2017.
These special conditions are issued for the General Electric (GE) GE9X turbofan engine models. These engine models will have novel or unusual design features associated with composite fan blades. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for these design features. 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.
80 FR 72561 - Special Conditions: CFM International, LEAP-1B Engine Models; Incorporation of Woven Composite Fan Blades
FR Doc. 2015-29589
Docket No. FAA-2015-4220
Special Conditions No. 33-017-SC
The effective date of these special conditions is December 21, 2015. We must receive your comments by December 7, 2015.
These special conditions are issued for the CFM International (CFM), LEAP-1B engine models. This engine model will have a novel or unusual design feature associated with the engine: woven composite fan blades. 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.
80 FR 38913 - Special Conditions: Pratt and Whitney Canada, PW210A; Flat 30-Second and 2-Minute One Engine Inoperative Rating
FR Doc. 2015-16713
Docket No. FAA-2015-1771
80 FR 32440 - Special Conditions: CFM International, LEAP-1A and -1C Engine Models; Incorporation of Woven Composite Fan Blades
FR Doc. 2015-14084
Docket No. FAA-2014-0637
Special Conditions No. 33-015-SC
Effective July 9, 2015.
These special conditions are issued for the CFM International (CFM), LEAP-1A and -1C engine models. These engine models will have a novel or unusual design feature associated with the engine fan blades—new woven composite fan blades. 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.
80 FR 30389 - Special Conditions: Pratt and Whitney Canada, PW210A; Flat 30-Second and 2-Minute One Engine Inoperative Rating
FR Doc. 2015-12986
Notice No. 33-15-01-SC
Send your comments on or before June 8, 2015.
This action proposes special conditions for the Pratt and Whitney Canada PW210A engine model. This engine will have a novel or unusual design feature—an additional one engine inoperative (OEI) rating that combines the 30-second and 2-minute OEI ratings into a single rating. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These proposed 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.
79 FR 68137 - Special Conditions: CFM International, LEAP-1A and -1C Engine Models; Incorporation of Woven Composite Fan Blades
FR Doc. 2014-27019
Notice No. 33-14-02-SC
Send your comments on or before December 29, 2014.
This action proposes special conditions for the CFM International (CFM), LEAP-1A and -1C engine models. These engines will have a novel or unusual design feature associated with the engine fan blades—new woven composite fan blades. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These proposed 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.
79 FR 65508 - Airplane and Engine Certification Requirements in Supercooled Large Drop, Mixed Phase, and Ice Crystal Icing Conditions
FR Doc. 2014-25789
RIN 2120-AJ34
Amendment Nos. 25-140 and 33-34
Effective January 5, 2015.
14 CFR Parts 25 and 33
The Federal Aviation Administration is amending the airworthiness standards applicable to certain transport category airplanes certified for flight in icing conditions and the icing airworthiness standards applicable to certain aircraft engines. The regulations will improve safety by addressing supercooled large drop icing conditions for transport category airplanes most affected by these icing conditions; mixed phase and ice crystal conditions for all transport category airplanes; and supercooled large drop, mixed phase, and ice crystal icing conditions for all turbojet, turbofan, and turboprop engines.
2014-10-31; vol. 79 # 211 - Friday, October 31, 2014
79 FR 64666 - Special Conditions: SNECMA, Silvercrest-2 SC-2D; Rated 10-Minute One Engine Inoperative Takeoff Thrust at High Ambient Temperature
FR Doc. 2014-25884
Docket No. FAA-2014-0376
Notice No. 33-014-SC
The effective date of these special conditions is December 1, 2014.
These final special conditions are issued for the SNECMA, Silvercrest-2 SC-2D engine model. This engine will have a novel or unusual design feature—an additional takeoff rating that increases the exhaust gas temperature (EGT) limit to maintain takeoff thrust in certain high ambient temperature conditions with one engine inoperative (OEI) for a maximum of 10 minutes. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These final 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.
79 FR 44321 - Special Conditions: SNECMA, Silvercrest-2 SC-2D; Rated 10-Minute One Engine Inoperative Takeoff Thrust at High Ambient Temperature
FR Doc. 2014-18074
Notice No. 33-14-01-SC
Send your comments on or before September 2, 2014.
This action proposes special conditions for the SNECMA, Silvercrest-2 SC-2D engine model. This engine will have a novel or unusual design feature—an additional takeoff rating that increases the exhaust gas temperature (EGT) limit to maintain takeoff thrust in certain high ambient temperature conditions with one engine inoperative (OEI) for a maximum of 10 minutes. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. The proposed 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.
78 FR 19982 - Special Conditions: Turbomeca Ardiden 3K Turboshaft Engine
FR Doc. 2013-07662
78 FR 15597 - Special Conditions: GE Aviation CT7-2E1 Turboshaft Engine Model
FR Doc. 2013-05676
Docket No. FAA-2012-0745
Special Condition No. 33-012-SC
The effective date of these special conditions is April 11, 2013.
These final special conditions are issued for the General Electric Aviation (GE) CT7-2E1 engine model. This engine model will have a novel or unusual design feature, which is a combination of two existing ratings into a new rating called “flat 30-second and 2-minute OEI” rating. This rating is intended for the continuation of flight of a multi-engine rotorcraft after one engine becomes inoperative. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These final special conditions contain the additional safety standards the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.
77 FR 66936 - Special Conditions: Turbomeca Ardiden 3K Turboshaft Engine
FR Doc. 2012-25214
Docket No. FAA-2012-1085
Notice No. 33-12-02-SC1
Send your comments on or before December 10, 2012.
This action proposes special conditions for the Turbomeca Ardiden 3K model engines. This engine model will have a novel or unusual design feature which is a 30-minute all engines operating (AEO) power rating for hovering at increased power (HIP). This rating is primarily intended for high-power hovering operations that are normal mission functions. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These proposed special conditions contain the additional safety standards that the FAA considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.
FR Doc. 2012-23105
RIN 2120-AF57
Amendment No. 33-33
Docket No. FAA-2012-0941
Technical amendment; correction.
This corrective action becomes effective September 20, 2012.
The FAA is correcting a technical amendment published on July 5, 2012 (77 FR 39623). In that technical amendment, the FAA clarified aircraft engine vibration test requirements in the airworthiness standards. The technical amendment was in response to inquiries from applicants requesting FAA engine type certifications and aftermarket certifications, such as supplemental type certificates, parts manufacturing approvals, and repairs. We revised the regulation to clarify that engine surveys require an engine test. Representatives of industry suggested that our technical amendment was in fact, a substantive change in the regulation, not a clarification. The FAA is correcting our prior action in response to that industry claim. This document amends the FAA&apos;s regulations to reverse the changes to § 33.83(a) amendment 33-33 and restore § 33.83(a) to its previous amendment 33-17.
2012-07-20; vol. 77 # 140 - Friday, July 20, 2012
77 FR 42677 - Special Conditions: General Electric CT7-2E1 Turboshaft Engine
FR Doc. 2012-17560
Notice No. 33-12-01-SC
Send your comments on or before September 18, 2012.
This action proposes special conditions for the General Electric CT7-2E1 engine model. This engine model will have a novel or unusual design feature which is a combination of two existing ratings into a new rating called “flat 30-second and 2-minute OEI” rating. This rating is intended for the continuation of flight of a multi-engine rotorcraft after one engine becomes inoperative. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These proposed special conditions contain the additional safety standards the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.
FR Doc. 2012-16290
This amendment becomes effective July 5, 2012.
This amendment clarifies aircraft engine vibration test requirements in the airworthiness standards. The clarification is in response to inquiries from applicants requesting FAA engine type certifications and aftermarket certifications, such as supplemental type certificates, parts manufacturing approvals, and repairs. We are revising the regulations to clarify that “engine surveys” require an engine test. The change is not substantive in nature, and will not impose any additional burden on any person.
77 FR 22187 - Technical Amendment; Airworthiness Standards—Aircraft Engines
FR Doc. 2012-8984
Amendment No. 33-32
This amendment corrects a number of errors in the airworthiness standards for aircraft engine endurance tests. None of the changes are substantive in nature, and none will impose any additional burden on any person.
77 FR - Special Conditions: Pratt and Whitney Canada Model PW210S Turboshaft Engine
FR Doc. C1-2011-14113