PART LIVES. At return, the condition of the Aircraft will be as follows: (CONFIDENTIAL MATERIAL OMITTED)
PART LIVES. At Delivery, the condition of the Aircraft will be as follows:
(a) The Aircraft will have zero hours consumed since completion of the Delivery Check.
(b) Each Engine will meet all of the following:
(i) Each Engine will have operated no more than hours and cycles since its last Qualified Performance Restoration.
(ii) Each Engine will have at least hours and cycles remaining to operate until its next anticipated removal (based on a review of the Engine historical and technical records and the results of the borescope inspection, trend monitoring and maximum power assurance runs).
(iii) Each Engine will have a remaining hot day takeoff EGT margin sufficient to permit the operation of such Engine for the hours and cycles set forth in the preceding subparagraph (based on a review of the Engine historical and technical records and the results of the borescope inspection, trend monitoring and maximum power assurance runs).
(iv) Each Part of an Engine which has a life limit will have cycles (or hours, if applicable) remaining to operate until its next removal per the Engine manufacturer’s limit.
(c) The APU will have zero APU hours consumed since the last hot section refurbishment (excluding hours consumed on the acceptance flight).
(d) Each leg of the Landing Gear will have at least two years and cycles remaining pursuant to the MPD until the next scheduled Overhaul or scheduled removal.
(e) Each Part of the Airframe, Engine or APU which has a hard time limit pursuant to the MPD will have the greater of (i) at least 50% of such hard time Part’s full allotment of hours and cycles or (ii) hours and cycles remaining to operate until its next scheduled Overhaul or scheduled removal pursuant to the MPD. However, if such hard time Part’s full allotment of hours and cycles between Overhauls pursuant to the MPD is less than hours and , then such hard time Part will be delivered with zero hours and zero cycles out of Overhaul.
(f) Each life-limited Part of the Airframe or the APU will have the greater of (i) at least 50% of such life-limited Part’s full allotment of hours and cycles or (ii) hours and cycles remaining to operate until its next scheduled replacement pursuant to the MPD (in case of an Airframe life-limited Part) or the APU’s manufacturer’s limit (in case of an APU life-limited Part). However, if such life-limited Part’s full allotment of hours and cycles remaining to operate is less than hours and cycles, then such life-limited Part will be delivered with 10...
PART LIVES. At return, the condition of the Aircraft will be as follows:
21.12.1 The Aircraft will have zero (0) hours consumed since the last zonal, systems and structural “C” check in accordance with the MPD (excluding hours consumed on the acceptance flight).
21.12.2 Each Engine will meet all of the following:
(a) Each Engine and each module thereof will have no more than Three Thousand (3,000) Flight Hours and One Thousand Five Hundred (1,500) Cycles consumed since its last Engine Performance Restoration Shop Visit.
(b) Each Engine and each Part of each Engine which has a life limit will not have operated more than One Thousand Five Hundred (1,500) Cycles since its last full disk stack replacement.
(c) Notwithstanding sub-sections (a) and (b) above, in case of a demonstrated unscheduled Engine removal, which will restrict Lessee’s ability to comply with the provisions in such sub-sections, Lessor will consider discussing in good faith with Lessee on a case by case basis, whether it could accept each Engine (and each module thereof) having not more than Five Thousand (5,000) Flight Hours consumed since its last Engine Performance Restoration Shop Visit and each life-limited part not having operated more than Two Thousand Five Hundred (2,500) Cycles since its last full disk stack replacement.
(d) Engine documentation will show full traceability to birth for each listed LLP.
21.12.3 The APU will be in good operating condition within maintenance manual limitations and have zero (0) hours consumed (excluding hours consumed during the acceptance flight) since the last Medium Repair or Heavy Repair in accordance with the manufacturer’s maintenance manuals (with any defects identified during such inspection corrected). APU documentation will show full traceability to birth for each listed LLP.
21.12.4 The Landing Gear will have no more than Three (3) months utilization since its last Overhaul pursuant to the MPD. Landing Gear documentation will show full traceability to birth for each listed LLP.
21.12.5 Each component or Part of the Airframe (except the Landing Gear) which has a hard time (hour/cycle or calendar) limit to Overhaul pursuant to the MPD will have not less than Four Thousand Seven Hundred Fifty (4,750) Flight Hours, Two Thousand Seven Hundred Fifty (2,750) Cycles or Eighteen (18) months, whichever is the most limiting factor, remaining to operate until its next scheduled Overhaul pursuant to the MPD.
21.12.6 Each LLP of the Airframe not already covered under...
PART LIVES. At return, the condition of the Aircraft will be as follows:
23.12.1 The Aircraft will have zero hours consumed since the Return Check (excluding hours consumed on the acceptance flight). In addition, for each “HMV Task” that was not performed at the Return Check, LESSEE will pay LESSOR an amount equal to the number of hours, cycles, or calendar days (whichever is the relevant determining factor for such HMV Task pursuant to the MPD) consumed on the Aircraft at return since Delivery (or if, such
PART LIVES. At return, the condition of the Aircraft will be as follows:
23.11.1 The Aircraft will have zero (0) hours consumed since the Return Check (excluding hours consumed on the acceptance flight).
23.11.2 Each Engine will meet all of the following:
(a) Each Engine will have at least 4,000 hours and 3,500 cycles remaining to operate until its next anticipated removal (based on a review of the Engine historical and technical records, borescope inspection results, power assurance run results, trend monitoring data and the other checks specified in Articles 23.10.7, 23.10.8, 23.10.9 and 23.10.10).
PART LIVES. The condition of the Aircraft and installed systems will be as follows:
(1) The Aircraft shall be returned with no more time since the last "C7" Check including the 20,000 hour structural inspection items or the equivalent heaviest maintenance inspection (complete block overhaul) as provided at the Delivery Date. Lessee may return the Aircraft with more time since last "C7" Check provided Lessee pays Lessor the difference between the time since the last "C7" Check upon delivery and the actual time since "C7" Check upon return, times the Airframe Maintenance Reserve Amount. However, in no event shall the Aircraft have less than one "C" Check interval remaining until the next "C7" Check. Airframe Maintenance Reserves may be used to offset this amount.
(2) Each Engine shall be returned with the same time remaining or more time remaining until the next restriction as at the Delivery Date. Each Engine shall have no more time since last heavy shop visit, last hot section refurbishment and last cold section refurbishment as at the Delivery Date. Engine disk sheets shall be used for reference.
(3) Each landing gear will be serviceable. Each landing gear shall be returned with the same amount of time remaining or more time remaining until the next restriction as at the Delivery Date. Lessee may return a landing gear with less time remaining until the next restriction provided Lessee pays Lessor the difference between the time remaining until the next restriction upon delivery and the time remaining until the next restriction upon return times the Landing Gear Reserve Rate. Landing Gear Reserves may be used to offset this amount. However, in no event shall any single landing gear have less than one (1) "C" Check interval remaining.
(4) Each APU will be returned in serviceable condition and shall pass borescope.
(5) Each Component (excluding the Engines but including any components thereon) will be returned in serviceable condition with at least 3,000 hours or cycles or twelve (12) months remaining, whichever is more limiting. EXHIBIT D to Aircraft Lease Agreement CERTIFICATE AS TO STATUS OF AIRCRAFT FIRST SECURITY BANK, N.A., not in its individual capacity, but solely as owner trustee ("Lessor"), and FRONTIER AIRLINES, INC., a Colorado corporation ("Lessee"), hereby certify as follows:
1. Lessor and Lessee are parties to that certain Aircraft Lease Agreement dated February 26, 1999 (the "Lease"), with respect to the Boeing 737-200A commercial jet aircraft bearing ma...
PART LIVES. SEE PARAGRAPH 17 OF EXHIBIT C.
23.9.1 SEE PARAGRAPH 17(a) OF EXHIBIT C.
23.9.2 SEE PARAGRAPH 17(b) OF EXHIBIT C.
(a) SEE PARAGRAPH 17(b)(i) OF EXHIBIT C.
(b) SEE PARAGRAPH 17(b)(ii) OF EXHIBIT C.
(c) SEE PARAGRAPH 17(b)(iii) OF EXHIBIT C.
(d) SEE PARAGRAPH 17(b)(iv) OF EXHIBIT C.
(e) SEE PARAGRAPH 17(b)(v) OF EXHIBIT C.
PART LIVES. At return, the condition of the Aircraft will be as follows:
(a) Article 23.9.
1. The Aircraft will have [Redacted] since the last full and complete zonal, systems and structural check (“C” check or equivalent) (excluding hours consumed on the acceptance flight).
(b) Article 23.9.2. Each Engine will meet all of the following:
(i) Article 23.9.2
(a) Each Engine will have [Redacted] until its next anticipated removal, based upon (a) [Redacted], (b) the Engine manufacturer’s estimated mean time between removals for engines of the same type as the Engines, and (c) the number of hours and cycles that each of the respective Engines has operated since [Redacted].
(ii) Article 23.9.2(b) Each Engine will have a [Redacted] sufficient to permit the operation of such Engine for the hours and cycles set forth in the preceding subparagraph, based upon the historical experience of the Engine manufacturer’s worldwide fleet.
(iii) Article 23.9.2(c) No [Redacted] will have [Redacted] than such [Redacted].
(iv) Article 23.9.2(d) Each Part of an Engine which has a hard time limit will have [Redacted] remaining [Redacted]. Notwithstanding the foregoing, any such Engine Part may be returned with [Redacted], provided that (i) no such Part will have [Redacted], and (ii) for each such Part, [Redacted].
(v) Article 23.9.2(e) Each Part of an Engine which has a life limit will have [Redacted].
(c) Article 23.9.3. The [Redacted] will have no more than [Redacted].
(d) Article 23.9.4. The [Redacted] will have at least [Redacted], provided that in all events the [Redacted].
(e) Article 23.9.5. Each Part of the Aircraft [Redacted] which has a [Redacted] will have at least [Redacted]. Notwithstanding the foregoing, any such Part may be returned with [Redacted], provided that:
(i) Article 23.9.5(a) no such Part will have [Redacted],
(ii) Article 23.9.5(b) for each such Part, [Redacted], and
(iii) Article 23.9.5(c) [Redacted].
(f) Article 23.9.6. Each life-limited Part of [Redacted] will have at least [Redacted]. Notwithstanding the foregoing, any such Part may be returned with less than [Redacted], provided that:
(i) Article 23.9.6(a) no such Part will have [Redacted],
(ii) Article 23.9.6(b) for each such Part, [Redacted], and
(iii) Article 23.9.6(c) [Redacted].
(g) Article 23.9.7. Each Part which [Redacted] after return of the Aircraft to LESSOR (which in any event will be [Redacted]). If a Part has [Redacted]l, then such Part will be returned with [Redacted].
(h) Article 23.9.8. No Part o...
PART LIVES. At return, the condition of the Aircraft will be as follows:
(a) The Aircraft will have zero (0) hours consumed since the last full and complete zonal, systems,
PART LIVES. At return, the condition of the Aircraft will be as follows:
23.9.1 The Aircraft will have zero (0) hours consumed since the last full and complete zonal, systems and structural check ("C" check or equivalent) (excluding hours consumed on the acceptance flight).
23.9.2 Each Engine will meet all of the following:
(a) Each Engine will have operated no more than 4,000 hours and 4,000 cycles since the last full performance restoration shop visit in which the core modules (including without limitation the high pressure compressor rotor and stator, combustor, stage 1 nozzle and high pressure turbine assembly) were fully refurbished and will have at least 6,000 hours and 6,000 cycles remaining until its next anticipated removal (based upon the Engine manufacturer's estimated mean time between removals for engines of the same type as the Engines); provided, however, that if at the time of return Engine manufacturer's mature mean time between removal rate for engines of the same type as the Engines is greater than 10,000 hours and 10,000 cycles, then the above referenced 4,000 hour and 4,000 cycle requirement will be increased by an amount equal to the difference between (i) the number of hours and cycles of such mean time removal rate and (ii) 10,000 hours and 10,000 cycles (for example, if at return the mature mean time removal rate is 14,000 hours and 14,000 cycles, each Engine will have operated no more than 8,000 hours and 8,000 cycles since its last full performance restoration shop visit and will have at least 6,000 hours and 6,000 cycles remaining until its next anticipated removal).
(b) Each Engine will have a remaining EGT margin sufficient to permit the operation of such Engine for the hours and cycles set forth in the preceding subparagraph, based upon the historical experience of the Engine manufacturer's worldwide fleet;
(c) No life-limited Part of an Engine will have more hours or cycles consumed than such Engine's data plate; and
(d) Each Part of an Engine which has a hard time limit will have at least 50% of such Part's full allotment of hours and cycles remaining to operate until its next scheduled Overhaul. Each Part of an Engine which has a life limit will have at least 50% of such Part's full allotment of hours and cycles remaining to operate until its removal. However, if 50% of such hard time or life-limited Part's full allotment of hours and cycles remaining is less than 6,000 hours and 6,000 cycles, then such hard time or life-limited Part ...
