APPENDIX 1 A1-1
Appendix 1 AIRWORTHINESS COMPLIANCE CHECKLIST #1: INSTALLATION OF APPROVED BELT DRIVEN GENERATORS AND ALTERNATORS Other Guidance AC 43-13-1B/2A TABLE 1-1. Installation of Approved Belt Driven Generators and Alternators - Checklist Qualifications for DER Data Review AC Orders Policy DER Authority [3] (ref. 8110.37
a. I have determined the planned alteration to be in compliance with paragraph d, checklist applicability. DATE MODEL N# Item to Consider Intent of the regulation • Determine suitability of each component on safety of essential systems. • Alternator type, belt type etc., must be suitable for the aircraft and its intended • All materials must meet suitable • Inspection and servicing must be accomplished in an appropriate manner. • Are reasonable means provided for inspection and servicing. • Approved for mounting. • Use provisions for mounting. • Electrical sparking contact with flammable fluids or vapors mist minimized. • Continued rotation during a malfunction, if hazardous, must have a means to prevent rotation without interfering with the continued operation of the engine. • Additional equipment installed (per operating rules) must meet intended operation. specifications. function.
3.291 3.292 3.296 3.635 3.651
23.601 23.603 N, 17, 23 23.611 N, 7, 48 123.1153 N, 14, 29, 34, 42 23.1301 N, 7, 14, 20 Design and Construction, General Materials and Workmanship Inspection Provisions [4] Powerplant Accessories Function and Installation CERTIFICATION BASIS DATE ON TDCS_ Planned FAA Approval Method Other 8110-3 337, Block 3 (AC 43.13) Pick 1, [2] FSDO ASI, IA SIGNATURE AIRCRAFT MAKE SERIAL # Item [1] DER Completed Initials A1-2
Appendix 1 TABLE 1-1. Installation of Approved Belt Driven Generators and Alternators - Checklist Qualifications for DER Data Review (continued) Other Guidance AC Orders AC 43-13-1B/2A Policy Loads analy sis AC or MIL spec or may apply all equipment and current from alternator.
DER Authority 13] (ref. 8110.37 Item to Consider Intent of the regulation • May not interfere with operation of equipment essential to safe operation, or other equipment unless there is a means to inform pilot. • Examine electrical system, charging and distribution separately and in relation to other systems, warning, engine instruments, etc. • All equipment determined as essential must be taken into account in the load analysis. • Must be labeled as to identity, function, operation, operational limits, or any combination thereof. AMBER: Caution lights (lights indicating the possible need for future corrective action.) • Alternator and associated transmission cable must be rated for the loads applied to the electrical system in probable combinations and durations. • Reverse current cutout will not allow the battery to drain if alternator fails. • If fused, must carry a spare fuse. • Must be locatable and identifiable in flight for reset or replacement.
CE 3.652, 3.681 3.690, 3.687 3.690, 13.691 DI) 23.1309 14, 17, 34, 41, 49 23.1322 17, 43 23.1351 N. 7. 14. 17, 20, 34 23.1357 N, 20, 43 Hazard Assessments Warning Lights System Reverse Current Cutout Circuit Protective Devices Planned FAA Approval Method Other 8110-3 337, Block 3 (AC 43.13) Pick 1, [2] FSDO ASI, DER Item [1] Completed Initials A1-3
Appendix 1 TABLE 1-1. Installation of Approved Belt Driven Generators and Alternators - Checklist Qualifications for DER Data Review (continued) Other Guidance DER AC Authority Orders [3] (ref. AC 43-13-1B/2A Policy 8110.37 [1] IA should enter initials to indicate items that have been completed. In some cases items may be left open pending final FSDO/ASI signature in [2] These findings can be made by a FSDO inspector, ACO engineer or DER. When FSDO inspector approves an item they must also sign For certification basis other than listed in columns 6 or 7, such as CAR 4 or Bulletin 7, etc., write in this column. For more information see Item to Consider or Intent of the regulation • Master switch arrangement shall be provided which will disconnect all sources of electrical power from the main distribution system at a point adjacent to the power sources. • Master switch will be easily discernable • All switches must be capable of handling the required current. • Constructed with enough distance or insulating material between parts and housing so that vibration is not a problem. • Accessible to appropriate flight crewmembers. • Labeled as to operation and the circuit controlled. • Must include procedures for removal and installation from aircraft (i.e. exploded view, wiring diagrams, etc.). • Special tools required. • Encouraged to include required inspection interval. • May include repair of equipment component if not on replace as required basis. Equipment OEM manuals are encouraged but not alone acceptable.
3.688, 3.689 3.694 [4] The amendment numbers are shown I italics. For more information see section 7.
23.1361 N, 20, 43, 23.1367 23.1529 49 [3] Or other equivalent authority, as evident on this form per DER.
Master Switch Switches Instruction for Continued Airworthiness Planned FAA Approval Method Other 337, Block 3 (AC 43.13 Pick 1, [2] FSDO ASI, DER 8110-3 Block 3 of FAA Form 337. Block 3 of FAA Form 337.
Item [1] Completed Initials section 7.
[5]
Appendix 1 TABLE 1-2. Comparison for Applicability Issues Installed Alternator/Generator Aircraft Alternator/Generator Weight C.G Installation Operational RPM Heat Disposition Capacity Rotation Direction Noise Filter Amperage Rating Band Pass Filter Amperage Rating Safety Lock Wire or Bend over Tabs on Component Belt and Pulley Alignment Key or Keyway Belt Size/Type Noise Filter Rating [1] When installing larger capacity alternator the following items may need to be addressed: • Larger belts are often required. • Alternator cooling air may not be sufficient. • Master electrical system breakers may need replacing • Charging current wires may need replacing • Battering charging cables may need replacing. [2] If the new alternator has an internal voltage regulator and the original did not, additional electrical systems investigation will most likely have to be done. Contact an electrical system DER.
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Appendix 1
b. Checklist Table. This checklist is issued for guidance purposes to help show completeness of documentation for the FAA field approval and return to service process. The checklist is intended to provide guidance information during the approval process and then returning the airplane to service. An airplane alteration is eligible to use this checklist when it has met the requirements outlined in paragraph 8d of this AC.
c. Approval. Alterations meeting the scope described in paragraph c may be approved by using this checklist and completing FAA Form 337. The IA can approve this alteration return to service using DER data entirely approved by completing Block 7, “Approval for Return to Service,” of FAA Form 337. The FAA usage of Block 3, “For FAA Use Only,” will not be required to accomplish this checklist for alterations that fall within the scope of paragraph c, providing that no data approval is required by AFS/ASI. Should an IA have any questions about the applicability or use of this checklist, they are encouraged to consult with their local FSDO.
d. Checklist Applicability. This alteration must be in compliance with paragraph 8d of this AC, which outlines all the limitations, restrictions and requirements that are applicable to all checklists. This checklist is to be used only on alterations to the following:
• Airplanes of 6,000 pounds or less maximum gross weight
• Airplanes having a single, naturally aspirated reciprocating piston engine
• Unpressurized airplanes
• Belt driven installations of alternator or generator only.
e. Checklist Use. Inspect the alteration and examine its supporting data to verify that they meet the following criteria:
(1) The FAA Form 337 must include engineering analysis to support applicability of installation to aircraft application. Such engineering analysis should include weight, installation, operational Revolutions Per Minute (RPM), heat dissipation compatibility, amperage output compatibility and operational rotation direction compatibility.
(2) If the new alternator or generator replaces an existing alternator or generator, utilize Table 1-2 for applicability issues.
(3) Appropriate operational advisory information should be included in the AFM or FMS.
(4) Many aircraft installations have noise filters installed on the aircraft firewall or firewall area. These filters have amperage ratings that should not be exceeded by the amperage increases of newly installed generators or alternators.
(5) When installing generators or alternators with increased amperage output from original, use the drive belt of the smaller original unit. This will maintain the original failure mode characteristics of the original installation.
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Appendix 1
(6) Installation must comply with installation instructions and limitations of component manufacture and aircraft standards.
(7) Any additional ICAs are properly documented per 14 CFR, part 23, § 23.1529, requirements.
f. Necessary Approvals.
(1) All initials must be complete in column one, with “Planned FAA Approval Method” selected in column 2-4.
(2) If column 3 is selected on any item, Block 3 of the FAA Form 337 must be signed by an ASI.
(3) An ACO engineer or FSDO inspector may sign in place of any DER signature on any data approval.
g. Applicable Guidance Material.
h. Evidence of DER Authority to Approve.
i. Complete Checklist Process. Send a copy of the completed checklist and reporting data to the local FSDO office, which will, in turn, forward it to the FAA Aircraft Registration Branch, Oklahoma City, Oklahoma, for inclusion in the aircraft record. Submit originals to the aircraft owner or operator to be kept with the aircraft records.
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Appendix 1 AIRWORTHINESS COMPLIANCE CHECKLIST #2: ALTERNATE FUEL AND OIL LINE FABRICATIONAND INSTALLATION Other Guidance AC AC 43-13-1B/2A Orders Policy TABLE 2-1. Alternate Fuel and Oil Lines - Checklist Qualifications for Approved Data Review DER Authority [3] (ref. 8110.37
a. I have determined the planned alteration to be in compliance with paragraph d, checklist applicability. DATE MODEL N# Item to Consider Intent of the regulation Limit load is maximum in service. • Analysis to LIM must produce no yield. Weight for test = bracket structure + associated hoses + oil in hoses. • Ultimate = Limit load * 1.50 (50 percent • LIM with no yield • ULT with no failure. Limit loads are determined by flight (man. and gust) and landing loads. For lack of this data the loads from 23.561 may be used but not required. • All materials must meet approved • Hoses in fire area per TSO-C53a, type • All non-standard aircraft hardware to be • Baffle material to withstand engine heat (i.e.silicone impregnated fiberglass). • Grommets, firewall bulkhead fittings, etc. • Inspection and servicing must be accomplished in an appropriate manner.
margin of safety) specifications. C/D. substantiated.
3.171 3.172 3.173 3.174 3.292 3.296
23.301 N, 28, 42, 48 23.303 23.305 N, 45 23.307 23.603 23.611 N, 7, 48 Loads Factor of Safety Strength and Deformation Proof of Structure Materials and Workmanship Inspection Provisions CERTIFICATION BASIS DATE ON TDCS _ Planned FAA Approval Method Other 337, Block 3 (AC 43.13 Pick 1, [2] FSDO ASI, IA SIGNATURE AIRCRAFT MAKE SERIAL # Item [1] DER Completed 8110-3 Initials A1-8
Appendix 1 TABLE 2-1. Alternate Fuel and Oil Lines - Checklist Qualifications for Approved Data Review (continued) Other Guidance DER AC 43-13-1B/2A AC Authority Orders [3] (ref. Policy 8110.37 [1] IA should enter initials to indicate items that have been completed. In some cases items may be left open pending final FSDO/ASI signature in Block 3 [2] These findings can be made by a FSDO inspector or DER. When FSDO inpector approves an item they must also sign Block 3 of FAA Form 337. [5] For certification basis other than listed in columns 6 or 7, such as CAR 4 or Bulletin 7, etc., write in this column. For more information, see section 7.
Item to Consider CE Intent of the regulation 3.433 • Use hose of equal or greater size. 3.55 • Support line so that no excessive vibration occurs. • Provisions for flexibility for relative motion. Limitations of flexible hose. 3.172 • Protect hoses from wheels up landing tri gear. 13.173 • LIM with no yield • ULT with no failure • Do not create new "low spots". 3.174 3.57 • Excessive vibration. • Flow rate, install equal or larger size. • Breather lines must: • Not allow condensation to freeze and obstruct line. • Not constitute fire hazard from forming. • Not allow omitted oil from striking windshield. • Not discharge into induction air intake. • Not be prone to blockage by ice. • See separate guidance. 4] The amendment numbers are shown in italics. For more information see section 7.
₺I) 23.955 Fuel N, 7, 43, Flow 23.993 Fuel System N, 43 Lines and Fittings 23.994 Fuel System 7, 29 Components 23.305 Strength and N, 45 Deformation 23.999 Fuel System N, 17, 43 Drains 23.1017 Oil System N, 7, 14 Drain 23.1529 Instructions 8. 26 for Continued Airworthiness [3] Or other equivalent authority, as evident on this form per DER.
Planned FAA Approval Method Other 337, Block 3 (AC 43.13 Pick 1, 12 FSDO ASI, DER 8110-3 of FAA Form 337.
Item [1] Completed Initials A1-9
Appendix 1
b. Checklist Table. This checklist is issued for guidance purposes to help show completeness of documentation for the FAA field approval and return to service process. The checklist is intended to provide guidance information during the approval process and then returning the airplane to service. An airplane alteration is eligible to use this checklist when it has met the requirements outlined in paragraph 8 of this AC.
c. Approval. Alterations meeting the scope described in paragraph d may be approved by using this checklist and completing FAA Form 337. The IA can approve this alteration return to service using DER data entirely approved by completing Block 7, “Approval for Return to Service,” of FAA Form 337. The FAA usage of Block 3, “For FAA Use Only,” will not be required to accomplish this checklist for alterations that fall within the scope of paragraph c, providing that no data approval is required by AFS/ASI. Should an IA have any questions about the applicability or use of this checklist, they are encouraged to consult with their local FSDO.
d. Checklist Applicability. This alteration must be in compliance with paragraph 8 of this AC, which outlines all the limitations, restrictions and requirements that are applicable to all checklists. This checklist is to be used only on or alterations to the following:
• Airplanes of 12,500 pounds or less maximum gross weight.
e. Checklist Use. Inspect the alteration and examine its supporting data to verify that they meet the following criteria:
(1) Installation must comply with installation instructions and limitations of component manufacture and aircraft standards.
(2) Any additional ICAs are properly documented per 14 CFR, part 23, § 23.1529, requirements.
f. Necessary Approvals.
(1) All initials must be complete in column one with “Planned FAA Approval Method” selected in column 2-4.
(2) If column 3 is selected on any item, Block 3 of the FAA Form 337 must be signed by the ASI.
(3) An ACO engineer or FSDO inspector may sign in place of any DER signature on any data approval.
g. Applicable Guidance Material.
h. Evidence of DER Authority to Approve.
i. Complete Checklist Process. Send a copy of the completed checklist and reporting data to the local FSDO office, which will, in turn, forward it to the FAA Aircraft Registration Branch, Oklahoma City, Oklahoma, for inclusion in the aircraft record. Submit originals to the aircraft owner or operator to be kept with the aircraft records.
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Appendix 1 Other Guidance AC 43-13-1B/2A AC Orders Policy TABLE 3-1. Relocation of Airplane Storage Batteries- Checklist Qualifications for Approved Data Review DER Authority [3] (ref. 8110.37 AIRWORTHINESS COMPLIANCE CHECKLIST #3: RELOCATION OF AIRPLANE STORAGE BATTERIES a. I have determined the planned alteration to be in compliance with paragraph d, checklist applicability. DATE MODEL N# Item to Consider Intent of the regulation • Limit load is maximum in service. • Analysis to LIM must produce no yield. margin of safety) • Load test to limit is okay, deformed permanently. • DO NOT TEST TO ULTIMATE conditions for flight test article. If tested to ultimate conditions the article must be thrown out or be tested to verify integrity. • Limit loads are determined by flight manual, gust, and landing loads. For lack this data the loads from 23.561 may be used (but not required). • The suitability of each questionable design detail and part having an important bearing on safety in operations, must be established by tests. • Inspection and servicing must be accomplished in an appropriate manner. • See separate guidance.
[5] 3.171 13.172 13.173 13.174 3.291 3.296 ₺I) 23.301 N, 28, 42, 48 23.303 23.305 N. 45 |23.307 123.601 |23.611 23.1529 Loads Factor of Safety Strength and Deformation Proof of Structure Design and Construction, General Inspection Provisions Instruction for Continued Airworthiness CERTIFICATION BASIS DATE ON TDCS Planned FAA Approval Method Other 337, Block 3 (AC 43.13) Pick 1, [2] FSDO ASI, IA SIGNATURE AIRCRAFT MAKE SERIAL # Item [1] DER Completed Initials 8110-3 A1-11
Appendix 1 Other Guidance AC 43-13-1B/2A TABLE 3-1. Relocation of Airplane Storage Batteries- Checklist Qualifications for Approved Data Review (continued) AC Orders Policy DER Authority [3] (ref. 8110.37 Item to Consider Intent of the regulation Additional equipment installed (per operating rules) must meet intended function. • Each electrical system must be adequate for the intended use. • Electric power sources, their transmission cables, and their associated control and pro- tective devices, must be able to furnish the required power at the proper voltage to each load circuit essential for safe operation • A protective device for a circuit essential to flight safety may not be used to protect any other circuit. • If the ability to reset a circuit breaker or replace a fuse is essential to safety in flight, that circuit breaker or fuse must be so located and identified that it can be readily reset or replaced in flight. For fuses identified as replaceable in flight: (1) There must be one spare of each rating or 50 percent spare fuses of each rating, whichever is greater; and (2) The spare fuse(s) must be readily accessible to any required pilot.
[5] 3.652 3.690 3.691 3.692
23.1301 N, 7, 14, 20 23.1351 N, 7, 14, 17, 20, 34, 43, 49 23.1357 N, 20, 21, 49 palans Function and Installation Electrical System Capacity Circuit Protective Devices Planned FAA Approval Method Other 8110-3 337, Block 3 (AC 43.13) Pick 1, [2] FSDO ASI, DER Item [1] Completed Initials A1-12