T E N D E R D O C U M E N T

Transcription

1 T E N D E R D O C U M E N T PERFORMING C-01 PHASE CHECK PACKAGE OF B ER AIRCRAFT REGN. S2-AFO & S2-AFP FOR BIMAN BANGLADESH AIRLINES LTD. INVITATION FOR TENDER NO: DACMP/001/2014 ISSUED ON: Page 1 of 64

2 Index list Section 1 : Instruction to Tenderers Section 2 : Tender Data sheet Section 3 : Particular Conditions of Contract Section 4 : General Specifications Section 5 : Work Package Page 2 of 64

3 Section-1 Section 1 : Instruction to Tenderers 1.1. Biman Bangladesh Airlines Limited invites Technical and Financial offers in sealed envelope from Airlines or Maintenance Organizations having in-house capability to perform C-Checks and its multiple checks or equivalent Check on Boeing ER aircraft for accomplishment of C-01 Phase Check Packages on two (02) Biman s ER aircraft as per work package of aircraft Registration: S2-AFO & S2-AFP. The tender schedule contains total 64 pages including the cover page. Tenderer must provide all information as per the requirements of the tender schedule Particulars of the aircraft: (i) First Aircraft a) Registration : S2-AFO b) MSN : c) Date of Manufacture : 20 October 2011 d) Present aircraft hours (as on ) : hrs e) Present aircraft cycles (as on ) : 1883 cyc f) Biman preferred slot for the check : 15 April 2014 g) Estimated hours and cycles the aircraft is Likely to attain on : FH & 2196 FC h) C-Phase Check interval : 36 Months (Per Biman Maintenance Program) (ii) Second Aircraft a) Registration : S2-AFP b) MSN : c) Date of Manufacture : 22 November 2011 d) Present aircraft hours (as on ) : hrs e) Present aircraft cycles (as on ) : 1813 cyc f) Biman preferred slot for the check : 10 May 2014 g) Estimated hours and cycles the aircraft is likely to attain on : FH & 2195 FC h) C-Phase Check interval : 36 Months (Per Biman Maintenance Program) Page 3 of 64

4 1.3. Tenderer's Qualification: (i). The Tenderer must have : a) Valid Certificate of Approval of FAA and/or EASA & approval from local Regulatory Authority for performing C-Check and multiple Checks or equivalent checks on B ER aircraft. b) Requisite facilities to perform C- Phase check Package on Boeing ER Aircraft as described in the work package. c) Performed at least seven (07) C-Checks or its multiple checks or equivalent checks on B ER during the preceding three (03) years period from January 2011 to December 2013 inclusive. Out of the 07 performed C-checks at least 03 checks must be performed on customers B aircraft. d) Track record of completing C-Check or its multiple Checks or equivalent checks on Boeing B ER Aircraft. (ii). In support of the Tenderer's qualification as stated in Para 1.3 (i), the Tenderer Must submit:- a. Documents in support of performing number of C-Checks or its multiple Checks performed on B ER aircraft in the preceding three (03) years, mentioning the Registration Mark and MSN of the aircraft and the date of commencement and completion of each check. b. Date of available hangar slots to perform C phase check within April May Note: Biman plan to perform C1- Phase check of first aircraft from 15 April 2014 and second aircraft from 10 May c. Tenderer shall provide copies of valid FAA and/or EASA approval and the approval of the local Regulatory Authority along with the offer. 1.4 Validity of Offer: The offer must be valid for 90 days from the closing date of submission of offer. 1.5 Submission of Offer: (i). The Offer to be submitted in a sealed envelope and must be addressed to: Director Engineering & Material Management Biman Bangladesh Airlines Ltd, Engineering Hangar Complex, HS International Airport, Dhaka-1229, Bangladesh. Page 4 of 64

5 The Tender documents must be submitted in the Tender Box located at Biman Hangar Gate (Gate # 8) by 1400 hours (LT) on 12 February 2014 or by courier service to the Director Engineering & Material Management to the address as mentioned in 1.5 (i). (ii) The envelope shall bear the following identification mark: C-01 Phase Check package of ER aircraft S2-AFO and S2-AFP (iii) The tender offer shall be in original and be signed and stamped in each pages. A copy of the tender offer (without having any deviation from the original) shall also be submitted along with original offer. (iv) The Tender Schedule/Document shall also be submitted along with tender offer duly signed and stamped in each pages. (v) A letter of undertaking as per specimen given below on the original Letter-head duly signed by an authorized person of the Tenderer shall be submitted along with the offer. Quote: I/We of M/S.. Owner / Owner's Representative hereby declare that I / We have understood and accept all the Terms and Conditions of the Tender Schedule and submitted quotation for each aircraft. I/We also hereby declared that I/we shall not provide any kind of inducement to any official of the tenderer. Unquote: Authorized Signature (s) with date Official Seal (v) Biman Bangladesh Airlines Ltd. reserves the right to accept or reject any or all the offers submitted by the Tenderers without assigning any reason whatsoever. 1.6 Opening of Tender The received offers will be opened at 1430 hours (LT) on 12 February 2014 in presence of Tenderers or their authorized representatives, if any. No offer would be accepted after the closing schedule. (Note: In case of opening date is declared as public holiday, Tender opening will take place on the next working day). The Tender opening shall take place at the following address: Conference Room, Biman Admin Building, Kurmitola, Dhaka-1229, Bangladesh. Time & Date: 1430 hours on 12 February 2014 Page 5 of 64

6 1.7 Evaluation criteria: Evaluation (Technical & Financial) of the tenders will be based on but not limited to, the following sections/sub-sections of the tender schedule: Section-1, Para-1.3, 1.4, & 1.5. Section-2, Para-2.5, 2.6, 2.7, 2.8 & 2.10 Section-3, Para- 3.1, 3.2, 3.3, 3.4, 3.5, 3.8, 3.9, 3.10 & Rejection of Tender Offer: Biman shall, exclude the Tenderer from participation or reject the tender offer and declare a Tenderer ineligible: i) If at any time determines that, the Tenderer has engaged in corrupt fraudulent, collusive or coercive practices in competing for, or in executing this contract tender. ii) Should any tender be found containing forged, false or in-genuine documents or information, the whole tender/ tender document will be rejected and the earnest money will be forfeited without serving any notice. Page 6 of 64

7 Section - 2 Tender Data Sheet A. General 2.1 The Employer: Biman Bangladesh Airlines Limited represented by Director Engineering & MM. Name of the Tender: C-01 Phase Check package for B ER aircraft S2-AFO and S2 -AFP B. Tender Document 2.2 Tender Notice and Tender Schedule can be viewed at Biman s website ( Tenderers will be required to download the Tender Schedule and prepare their offers as per requirement of the Tender Schedule. 2.3 Contact for any clarification of the Tender: Mr. A.R.M. Kaiser Zaman Dy. Chief Engineer Engineering Planning Address : Biman Hangar Complex, HS International Airport, Kurmitola, Dhaka-1229, Bangladesh. Telephone: address: dceep@bdbiman.com C. Preparation of Tender 2.4 The offer, as well as all correspondence relating to the Tender shall be in English language 2.5 The Tenderer shall submit a Draft agreement that shall comply with all Terms & conditions of the submitted offer. 2.6 Biman prefers performance of C-01 phase check within 10 days TAT. However, the Tenderer shall mention the TAT for the C-01 Phase Check package for each aircraft (S2-AFO and S2-AFP) but TAT shall not exceed 15 days. 2.7 Tenderer shall quote firm fixed price for C-01 phase check package of each aircraft separately. The fixed price shall remain valid for the duration of the Contract. The required financial offer shall include the following additional information: (i). Man-Hour rate for additional works. (ii). Payment terms. (iii). Any other information that may be required by the Tenderer. The Tenderer shall submit separate technical and financial offer for each aircraft (S2-AFO and S2- AFP) in one Envelope. Any subcontractor work, if required, must be accomplished by FAA/EASA approved organization. Page 7 of 64

8 D. Evaluation of offer 2.11 The evaluation condition shall be as follows : a) To determine technically responsive offer, all received offers shall be evaluated after application of all the technical evaluation factors indicated in Para 1.7. b) Among the responsive Tenderer(s) determined per para 2.11, the financially lowest tender offer shall be considered as successful Tenderer. Page 8 of 64

9 Section 3. Particular Conditions of Contract 3.1. Tenderer s Responsibility: Tender must agree the following: (i). (ii). (iii). (iv). Biman is operating two ER aircraft S2-AFO and S2-AFP. Biman has planned to perform its first C-01 phase check during the period of April-May Tenderer is to perform the C-01 Phase Check package as per the attached Work Package in Section -05. Tenderer shall undertake the responsibility to provide all components, parts, LRU s during the performance of C1 Phase check. Carry out necessary repair(s) for accomplishment of scheduled work and also un-scheduled work found necessary during performance of the scheduled inspection as per the supplied C-01 Phase Check package for the aircraft, S2-AFO and S2-AFP. Biman items may be removed from aircraft, restored and fitted back to aircraft. Any serialized component if provided by the Tenderer, full traceability back to birth history shall be provided for each component/lru. Alternately Tenderer is to provide the parts, components, LRU s on one-to-one exchange basis. The exchange items will be returned back to Tenderer when the aircraft returns to Dhaka after completion of C-01 Phase Check packages and on return of Biman original items duly restored by the Tenderer. All consumables, expendables and other materials/items required for performance of scheduled and unscheduled work found necessary during performance of scheduled inspection as per Work Package shall be provided by the Tenderer. (v). (vi). (vii). All nose cowls and fan reverser of engines are to be checked and inspected for their physical fitness and serviceability and to be repaired as required. All galleys and toilets, bulkheads, coat closets are to be checked and inspected and necessary repairs and painting shall be carried out by the Tenderer. The Tenderer shall supply all repair materials as required. Tenderer shall also perform any additional work that Biman may ask to perform during the C-01 Phase Check Package, without affecting TAT, such as any Service Bulletin, repair work, deferred defect rectification etc. (viii). After completion of C-01 Phase Check, the Tenderer must accomplish aircraft system Performance check where applicable, if required system check is to be carried out with engines test run. Page 9 of 64

10 (ix). The Tenderer must agree to comply with any and all directive/instruction issued by FAA and /or EASA and Civil Aviation Authority of Bangladesh (CAAB). (x). Tenderer shall agree to pay all local taxes, VAT and custom duty. (xi). The Tenderer must undertake six months Warranty on the performance of C-01 phase check on each aircraft. The Tenderer shall also warrant their subcontractor s work. 3.2 Price Quotation: Tenderers must quote the price in United States Dollars for the following: a). Fixed price for performance of the C 01 Phase Check Package of S2-AFO and S2-AFP as per the Work Package including all repairs and rectification found necessary including materials as per para. 3.1 (i), 3.1 (ii ) and 3.1 (iii ), 3.1 (iv ), 3.1 (v ), 3.1(vi), 3.1 (viii) and 3.1(ix) excluding price of Mod-Kits (which will be supplied by Biman) and any components declared Beyond Economical Repair (BER) having proper supporting documents. b). Man-hour rate for performance of any additional work if requested by Biman per Para. 3.1(vii). c). The Aircraft positioning from Tenderers airport to Tenderer s facility, hangaring, repositioning and all NRC (Non routine work card) raised during C-01 Phase Check packages will be included within firm and fixed price. 3.3 Turn Around Time: (i) (ii) (iii) The tenderer shall mention the maximum Turn Around Time (TAT) to perform the work packages of each aircraft: a) For S2-AFO -. days b) For S2-AFP -.. days For the purposes of calculating TAT, time shall commence from 0800 hours on the following morning after the delivery of the aircraft at the Tenderer s facility until the night before the redelivery of the aircraft at the Tenderer s facility on completion of final certification and re-delivery of the aircraft C-01 Phase Check package. Tenderer is to agree to provide Biman with real time update (progress) on the status of the aircraft being worked on and the flow chart plan to ensure TAT. Page 10 of 64

11 3.4 Payment Terms : i) Payment terms and conditions/ schedule shall be mentioned by the Tenderers. ii) All invoices related to Additional Works (if any) shall be prepared as per the rate/price as on the date of aircraft delivery but not on the date of invoice preparation. 3.5 Penalty: a) Tenderer must undertake to pay penalty US$ 10, (US Dollars Ten Thousand only) for each day by which re-delivery is delayed beyond the TAT, if the delay is caused by the Tenderer. b) The only other exception to Clause 3.5 (a) above shall be force majeure situation. 3.6 Tenderer Address & Person(s) to be Contacted: Tenderer must mention full mailing address and Telephone, Fax, and name & designation of the contacting person (s). 3.7 Work Records: A summary of the C-01 Phase Check Packages performed along with the original copies and a complete set of soft copies of completed schedule / un-schedule job cards duly signed by appropriate authorized person to be handed over to Biman representative during redelivery of the aircraft. All records must be in English language. 3.8 Customer's Authorized Representative: Biman's CAR (Customers Authorized Representative) together with Biman's qualified Engineers or Biman appointed experts shall be positioned at Tenderer's facility to monitor and oversee progress and quality of work and to co-ordinate with Tenderer to ensure smooth performance of the check to Biman's expectation and satisfaction in all respect. 3.9 Performance Guarantee: As performance guarantee for correctness, accuracy, standard and quality of work performed by the Tenderer, payment of 10% of the fixed price shall be held back for a period of six months after redelivery of the aircraft All correspondence/ communication with the tenderer shall only be made by authorized official of Biman Bangladesh Airlines Limited with the successful Tenderer. Page 11 of 64

12 3.11 Prior to proceeding any Additional Work beyond the work scope of Fixed Price (C-01 Work Package) the Tenderer shall take written permission from Biman Customer Authorized Representative (CAR). Section 4. General Specifications 4.1. Aircraft specification: (i). Registration : S2-AFO MSN : Date of Manufacture : 20 October 2011 Aircraft Type Manufacturer : B ER : BOEING (ii). Registration : S2-AFP MSN : Date of Manufacture : 22 November 2011 Aircraft Type Manufacturer : B ER : BOEING 4.2. Specification of consumable and components: a) All items used by tenderer must have serviceability Tag approved by FAA and/or EASA (FAA or EASA form one) or a serviceable Tag approved by Civil Aviation Authority of Bangladesh. b) All items/materials used by tenderer and all work done by tenderer must have approval of from Tenderers Local Regulatory Authority and Civil Aviation Authority of Bangladesh Details specification of work package: FORMAT LAY-OUT DESCRIPTION (i) DESCRIPTION OF COLUMNS: AMS Ref: DESCRIPTION: Lists the numerical sequence of the check items within the ATA Chapter. Gives a brief description of the work to be accomplished. The degree of disassembly as to be stated by assignment of access doors and other references (as Maintenance Manual and so on). For those items, Page 12 of 64

13 EFFECT: ZONES: INTERVAL: which are affected by an Airworthiness Directive, reference has to be given. NOTE, where given, states further requirements and/or provide useful information. ACCESS means the access panels or door numbers required to be opened when performing the task. The effectively of a task to a specific aircraft is stated by reporting the a/c registration number (last three digits). When effectively is left blank, it means ALL. It shows the area/zone in which the task has to be performed. They are indicated according to Manufacture s a/c zoning diagram in the a/c Maintenance Manual. After the last threshold, this is the maximum repeatable period allowed between subsequent task requirement accomplishments. Meaning of each code is detailed in paragraph 4.0 (Flight Hours, Cycles and so on). In some cases multiples of the check intervals (e.g. 2A, 2C and so on). Whenever task has an initial interval different from repetitive interval, it is shown underlined as: 1st = (initial).task intervals are specified in terms of a frequency and usage parameter such as flight hours, cycles, and calendar time. Letter checks are not used. FC: Airplane Flight Cycles APU CNG: APU Change FH: Airplane Flight Hours AHR: APU Hours DY: Days MO: Months YRS: Years IDG CNG: Integrated Drive Generator Change ENG CNG: Engine Change LDG CNG: Landing Gear Change LIF LIM: Life Limited NAT REQ: Regulatory Authority Requirement SHP VST: Shop Visit Threshold: The initial interval that the task is to be performed. Repeat: The repeat interval after the threshold interval has been reached. TASK: Codes defining type to be performed are reported in this column. Meaning of these codes is explained in paragraph 4. In the coding layout it has been considered that: The access and the degree of disassembly (if required) should be stated in DESCRIPTION COLUMN. Page 13 of 64

14 The subject to be examined must be cleaned if the normal degree of operational contamination is exceeded and a perfect check performance is not assured. Electrical tasks are used for inspection of electrical components, wiring, and panels and so on. If the task is clearly described in the DESCRIPTIOJN column, no task symbol may appear in this column. All tasks shall be accomplished in accordance with Boeing Maintenance Manual. (ii)task SYMBOLS CODING CODES GVI: TASK DESCRIPTION GENERAL VISUAL INSPECTION A visual examination of an interior or exterior area, installation or assembly to detect obvious damage, failure or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may require removal or opening of access panels or doors. Stands, ladders or platforms may be required to gain proximity to the area being checked. DVI/DET: DETAILED VISUAL INSPECTION: An intensive visual examination of a specific structural area, system, installation or assembly to detect damage, failure or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate by the inspector. Inspection aids such as mirrors, magnifying lenses, etc. may be used. Surface cleaning and elaborate access procedures may be required. SDI: SPECIAL DETAILED INSPECTION: An intensive examination of a specific item(s), installation or assembly to detect damage, failure or irregularity. The examination is likely to make extensive use of specialized inspection techniques and/or equipment. Intricate cleaning and substantial access or disassembly procedures may be required. OPC OPERATIONAL CHECK An operational check is a task to determine that an item is fulfilling its intended purpose. Does not require quantitative tolerance. This is failure- finding task. FNC FUNCTIONAL CHECK A quantitative check to determine if one or more function of an item performs with specified limits. This is a potential failure-finding task. RST RESTORATION Page 14 of 64

15 Reworking, replacement of parts or cleaning necessary to return an item to a specific standard. Restoration may vary from cleaning or replacement of single parts up to a complete overhaul. DIS DISCARD The removal of an item from service at a specified life limit. LUB/SVC LUBRICATION and SERVICING Any act of lubricating or servicing/ cleaning for the purpose of maintaining inherent design capabilities. Consumable replenishment by lubricating/servicing. VCK A visual check is an observation to determine that an item is fulfilling its intended purpose. Does not require quantitative tolerance. This is a failure finding task. BSI Borescope Inspection: Detailed examination under usage of borescopic tools. EWIS The term Electrical Wiring Interconnection System (EWIS) means any wire, wiring device, or combination of these, including termination devices, installed in the airplane for transmitting electrical energy between two or more termination points. EZAP MSR The Enhanced Zonal Analysis Procedures (EZAP) means attention to be given during electrical wiring installations. Thus, as well as determining zonal inspections, for zones that both contain electrical wiring and have potential for combustible materials being present an enhanced xonal analysis was performed. This enhanced zonal analysis provided a means to identify applicable and effective tasks to,imi,ize contamination and to address significant wiring installation discrepancies that may not be reliably detected through zonal inspection. Thus dedicated tasks are included in the Systems and Power plant requirement section of this AMS. Since these tasks are normally not system specific and do not have a Failure Effect Category, they have been included under ATA 20. Measurements with recording. Actual figures shall be noted and entered into the record book or cards The End Page 15 of 64

16 Section 5 : Work Package C-01 Phase Check Work package Contains: 1. System Task : Page 17 thru Structural Task : Page 36 thru Zonal Task : Page 40 thru Mod/Repair Task : page 64 thru 64 Page 16 of 64

17 SYSTEM TASK S/No AMS Task Task Description AMM REF. Zone Access Threshol Repeat MH Task Comments Lubricate the Leading Edge Slat Torque Tube Couplings, Supports and Gearbox Couplings PREP: Access to the torque tube coupling at the inboard end of the inboard no-back brake offset gearbox requires seal tube displacement. Lubricate the Forward Cargo Compartment Torque Tubes, Gearbox and Pressure Seal Couplings. PREP: Cargo sidewall liners 121SW, 122SW and cargo ceiling liners 121MC and 122GC removal required. LUBRICATE THE WING KRUEGER DRIVE ARM BEARING PREP: Extend leading edge slats to gapped position A 511CB 511GB 511MB 513AT 513BT 521AAB 521AB 521ACB 521BB 521DB 521EB 521FB 521GB 521HB 521JB 521KB 521LB 521MB 521PB 521QB 521RB 521TB 521VB 521WB 521YB 521ZB 611AB 611CB 611GB 611MB 613AT 613BT 621AAB 621AB 621ACB 621BB 621DB 621EB 621FB 621GB 621HB 621JB 621KB 621LB 621MB 621PB 621QB 621RB 621TB 621VB 621WB 621YB 621ZB 2.8 LUB 1.1 LUB 0.2 LUB Page 17 of 64

18 SYSTEM TASK S/No AMS Task Task Description AMM REF. Zone Access Threshol Repeat MH Task Comments LUBRICATE THE WING TRAILING EDGE TORQUE TUBES, TORQUE TUBE SUPPORTS, AND COUPLINGS (torque tube, gearbox, flap power drive, no-back brake, and transmission) PREP: Extend Trailing Edge Flaps To 30 Unit Position LUB Lubricate the Passenger Entry Door Mechanisms. PREP: Door liners 831AW, 831BW and escape slide pack 831CW removal required for Left door No.1. (Other doors are similar) LUBRICATE THE FORWARD ACCESS DOOR LATCH PIN AL 7 LUBRICATE THE MAIN EQUIPMENT CENTER ACCESS DOOR LATCH PIN. Inspect (Detailed) BRAKE CONTROL CABLES in exposed and unprotected areas, including wheel wells. PREP: Wheel well door 732 opened. Wheel well door 742 opened Inspect (Detailed Visual) of the foil/mesh in the engine cowls, strut and leading edge panels for degradation. This DV is for the left side of the airplane equipped with GE engines AL 0.35 LUB 0.1 LUB 0.1 LUB FH FH 1 DET AL 414AR 415AL 416AR 431DT 431ET 431FL 431FR 431FT 511AB 511CB 511DB 511EB 511FB 511GB 511HB 511JB 511KB 511LB 511MB 511NB 511PB 511QB 0.8 DET Page 18 of 64

19 SYSTEM TASK S/No AMS Task Task Description AMM REF. Zone Access Threshol Repeat MH Task Comments 423AL 424AR 425AL 426AR 441DT 441ET 441FL 441FR FT 611AB Inspect (Detailed Visual) of the foil/mesh in the engine cowls, CB 611DB strut and leading edge panels for degradation. This DV is for EB 611FB the right side of the airplane equipped with GE engines. 611GB 611HB 0.8 DET 611JB 611KB 611LB 611MB 611NB 611PB 611QB Functionally check (using Loop Resistance Tester or equivalent equipment) the left wing Actuator Control Electronics (ACEs) wire bundle shielding system from the ACEs to the various control surface power control units (PCUs) external to the pressure vessel (ailerons, flaperons, spoilers) BB 544CB 551DB 552AB 552BB 552FB 552HB 552LB 561NB 561PB 7 FNC Functionally check (using Loop Resistance Tester or equivalent equipment) the right wing Actuator Control Electronics (ACEs) wire bundle shielding system from the ACEs to the various control surface power control units (PCUs) external to the pressure vessel (ailerons, flaperons, spoilers) BB 644CB 651DB 652AB 652BB 652FB 652HB 652LB 661NB 661PB 7 FNC Functionally check (using Loop Resistance Tester or equivalent equipment) the Actuator Control Electronics (ACEs) wire bundle shielding system from the ACEs to the elevator and rudder power control units (PCUs), and to the Stabilizer Trim Control Modules (STCMs) external to the pressure vessel BL 313AL 324CL 324CXL 324DL 324DXL 324EL 324FL 324GL 335DB 335EB 335EX 335FB 335GB 335GXB 345DB 345EB 345EXB 345FB 345GB 345GXB FNC Page 19 of 64

20 SYSTEM TASK S/No AMS Task Task Description AMM REF. Zone Access Threshol Repeat MH Task Comments Functionally check (using LRT or equivalent equipment) the COAX shielding from the receiver and transceiver antennas to the Radio Altimeter transceivers. NOTE: a) Required for category 3B landing operations only. B) Airplane electrical power must be off Access : FNC Inspect (General Visual) the EWIS installed on the Forward bulkhead of the Left Main Landing Gear Wheel Well. (EZAP) PREP: Stands/ladders required for inspection GVI Inspect (General Visual) the EWIS installed on the Forward bulkhead of the Right Main Landing Gear Wheel Well. (EZAP) PREP: Stands/ladders required for inspection GVI Inspect (General Visual) the CARGO POWER DRIVE UNIT (PDU) WIRING and CONNECTED EWIS from floor level in the Forward Cargo Compartment. (EZAP) GVI Restore (Clean) the AREAS BEHIND the FORWARD CARGO COMPARTMENT SIDEWALL PANELS, zone 121/122. (EZAP) PREP: Sidewall liners 121DW -121SW, 122CW-SW removed RST Restore (Clean) The AREA BEHIND the FORWARD CARGO COMPARTMENT, zone 125/126. (EZAP) PREP: End wall liner 121TW removed RST Inspect (General Visual) the CARGO POWER DRIVE UNIT (PDU) WIRING and CONNECTED EWIS from floor level in the Aft Cargo Compartment (EZAP) GVI Page 20 of 64

21 SYSTEM TASK S/No AMS Task Task Description AMM REF. Zone Access Threshol Repeat MH Task Comments Restore (Clean) the AREAS BEHIND the PASSENGER COMPARTMENT AIR GRILLES for HIGH DENSITY seating in section 41 (36 or more passenger seats within the zone) (EZAP) 0.25 RST ACPREP: Air Grilles removed Inspect (General Visual) All WIRING and CONNECTED EWIS BEHIND the PASSENGER COMPARTMENT AIR GRILLES for HIGH DENSITY seating in section 41 (36 or more passenger seats within the zone). (EZAP) PREP: Air Grilles removed GVI Restore (Clean) the AREAS AROUND the VIDEO CONTROL CENTER located at door 2 cabin attendant area, if installed (EZAP) RST IInspect (General Visual) the EXTERNAL POWER RECEPTACLE, including CONNECTED EWIS, through Main Equipment Center Right Floor Panel. (EZAP). PREP: External Power Receptacle Guard removal required AF 0.5 GVI Restore (Clean) the AREAS BEHIND the PASSENGER COMPARTMENT AIR GRILLES for HIGH DENSITY seating in section 43 (54 or more passenger seats within the zone). (EZAP) PREP: Air Grilles removed Inspect (General Visual) All WIRING and CONNECTED EWIS BEHIND the PASSENGER COMPARTMENT AIR GRILLES for HIGH DENSITY seating in section 43. (EZAP) PREP: Air Grilles removed. Restore (Clean) the AREAS BEHIND the PASSENGER COMPARTMENT AIR GRILLES for HIGH DENSITY seating in section 44. (EZAP) PREP: Air Grilles removed RST 0.25 GVI 0.25 RST Page 21 of 64

22 SYSTEM TASK S/No AMS Task Task Description AMM REF. Zone Access Threshol Repeat MH Task Comments Inspect (General Visual) All WIRING and CONNECTED EWIS BEHIND the PASSENGER COMPARTMENT AIR GRILLES for HIGH DENSITY seating in section 44 (EZAP) GVI PREP: Air Grilles removed Restore (Clean) the AREAS BEHIND the PASSENGER COMPARTMENT AIR GRILLES for HIGH DENSITY seating in section 46. (EZAP) PREP: Air Grilles removed Inspect (General Visual) All WIRING and CONNECTED EWIS BEHIND the PASSENGER COMPARTMENT AIR GRILLES for HIGH DENSITY seating in section 46 (EZAP) PREP: Air Grilles removed. Restore (Clean) the AREAS BEHIND the PASSENGER COMPARTMENT AIR GRILLES for HIGH DENSITY seating in section 47 (36 or more passenger seats within the zone). (EZAP) PREP: Air Grilles removed Inspect (General Visual) All WIRING and CONNECTED EWIS BEHIND the PASSENGER COMPARTMENT AIR GRILLES for HIGH DENSITY seating in section 47. (EZAP) PREP: Air Grilles removed RST 0.2 GVI 0.25 RST 0.2 GVI Inspect (Detailed) AUXILIARY POWER UNIT (APU) STARTER POWER FEEDER CABLE and APU POWER FEEDER CABLE, including CONNECTED EWIS, in the APU compartment. (EZAP) AL 315BL 316AR 316BR 0.5 DET Inspect (Detailed) INTEGRATED DRIVE GENERATOR POWER FEEDERS and BACKUP GENERATOR POWER FEEDERS including CONNECTED EWIS, in Left engine. (EZAP) PREP: Cowls in open position AL 414AR 415AL 416AR 0.25 DET Inspect (Detailed) INTEGRATED DRIVE GENERATOR POWER FEEDERS and BACKUP GENERATOR POWER FEEDERS including CONNECTED EWIS, in Right engine. (EZAP) PREP: Cowls in open position AL 424AR 425AL 426AR 0.25 DET Page 22 of 64

23 SYSTEM TASK S/No AMS Task Task Description AMM REF. Zone Access Threshol Repeat MH Task Comments Operationally check the E/E Cooling System OVERRIDE FH FH 0.25 OPC SWITCH Functionally check the Air Conditioning Pack CONDENSER/REHEATER for flow restriction. NOTE: Applicable to airplane with P/N installed. Inspect (Detailed) E11 Rack SATCOM BACKUP FAN CHECK VALVES for freedom of movement, wear, condition and security FH FH 1 FNC FH 7500 FH 1 DET Inspect (Detailed) E11 Rack SATCOM BACKUP COOLING CHECK VALVE for freedom of movement, wear, condition and security FH FH 2 DET 40 Operationally check LANDING ALTITUDE MANUAL SELECT SWITCH. Inspect (General Visual) the Cabin Pressure Control System OUTFLOW VALVE DOORS, HINGES, and CONNECTING RODS for wear, condition, and security FH FH 1 OPC AL 117BL FH FH 0.5 GVI Functionally check (on or off-aircraft) POSITIVE PRESSURE RELIEF VALVES for correct set point FH FH 1.5 FNC Replace POSITIVE PRESSURE RELIEF VALVE FILTERS FH FH 0.5 DIS Functionally Check the AFT/BULK CARGO OVERHEAT PROTECTION SWITCH&RELAY. NOTE: Applicable to incorporation of SB A0038 PREP: Sidewall liner"161aw"removal required. Operationally check AC Pack Flow Control FLOW SENSOR (Delta-P Sensor) FH FH 1 FNC FH FH 0.5 OPC Page 23 of 64

24 SYSTEM TASK S/No AMS Task Task Description AMM REF. Zone Access Threshol Repeat MH Task Comments Clean (off-aircraft) AC Pack HEAT EXCHANGER EL 196ER FH FH 2 RST Functionally check (off-aircraft) AC Pack HEAT EXCHANGERS for leakage EL 196ER SHP VST SHP VST 2 FNC Inspect (Detailed) AC PACK FAN BYPASS CHECK VALVE FLAPPERS and HINGE PIN for freedom of movement, wear, condition, and security. PREP: When HEAT EXCHANGERS are removed for cleaning EL 196ER NOTE NOTE 1 DET Clean (off-aircraft) OZONE CONVERTERS. NOTE: Applicable to Ozone Converters Allied Signal P/N (Boeing P/N S213W291-2), P/N (Boeing P/N S213W291-4). Functionally check PASSENGER ADDRESS (PA) SYSTEM. (Individual Speakers) (Including Overhead Crew Rests) EL 196ER FH FH 0.5 RST FH FH 1.5 FNC installed P/N _ Honeywell Operationally check PASSENGER ADDRESS (PA) ALTERNATE CHANNEL on PA System. (Use PA NORM/ALT Switch.) FH FH 0.5 OPC Operationally check DIRECT ACCESS FUNCTION on Flight Attendants Panels.(Only on handsets with Direct Access Switch) Operationally check ALTERNATE CHANNEL of Cabin Interphone System. (Use CI NORM/ALT Switch.) Operationally check AUDIO TRANSFER SWITCH (Use OBS Audio Switch on P8 panel). Functionally check STATIC DISCHARGERS. (Measure resistance.) Functionally Check VOICE RECORDER SYSTEM for proper 4- channel operation FH FH 0.5 OPC FH FH 0.1 OPC FH FH 0.1 OPC FH FH 2 FNC FNC Page 24 of 64

25 SYSTEM TASK S/No AMS Task Task Description AMM REF. Zone Access Threshol Repeat MH Task Comments Functionally check voice recorder back up power system to ensure proper operation FH FH 0.4 FNC 212 Note: if installed Operationally check UNDERWATER LOCATOR BEACON on OPC Voice Recorder. (Use test equipment) 59 Functionally check the primary and secondary external power receptacle pins for excessive wear. Detailed inspection of the primary and secondary external power receptacle pins for signs of overheat and security of installation. 61 Operationally check MANUAL ADJUSTMENTS (vertical, horizontal) of the flight crew seats Operationally check PASSENGER SEAT BELTS to verify condition and security. (Also applicable to seats installed in Overhead Crew Rest area.) Operationally check the Crew Rest Bunk Belts and verify condition and security AR AR 0.3 FNC 0.3 DET FH FH 0.1 OPC FH FH 1 OPC FH FH 0.2 OPC Operationally check PASSENGER COMPARTMENT SEATS to verify that breakover and recline restrictions are satisfied FH FH 1 OPC Operationally check ATTENDANT SEAT RESTRAINT including INERTIA REEL and verify condition and security including restraints in the Flight Crew Rest FH FH 1 OPC Inspect and Hydrostatic test SLIDE INFLATION CYLINDER. INTERVAL NOTE: 03 years DL 198DR 3 YRS 3 YRS 2 GVI Restore OFF-WING EMERGENCY EVACUATION SLIDE ASSEMBLY at manufacturer's recommended interval. NOTE: a) Service life: 37 Months b) 37 months maximum time -in-service (ON-WING), with a 5 month allowance for shelf/ transportation time MO 37 MO 2.5 RST Page 25 of 64

26 SYSTEM TASK S/No AMS Task Task Description AMM REF. Zone Access Threshol Repeat MH Task Comments Operationally check the OFF-WING EMERGENCY ESCAPE SLIDE COMPARTMENT DOOR LOCK/LATCH SYSTEM (via the ground OPC 198 test port) Functionally check the OFF-WING ESCAPE SLIDE COMPARTMENT DOOR INDICATION SYSTEM, including the EICAS message indication. Operationally check EMERGENCY EVACUATION SIGNAL (EES) SYSTEM NOTE: Airplanes with EES System installed FH FH 0.3 FNC FH 7500 FH 0.5 OPC Perform a quality assurance sample of Boeing 777 SLIDE/RAFT system and supporting maintenance program. One sample set from the fleet should include a minimum of one operational check of an installed slide/raft from each door position, left or right, including overwing exits (if applicable), during each 3 year (1125 day) period. A different exit should be selected at each maintenance opportunity. The total sample set would be 5 doors. This sampling is to be continued until a satisfactory standard of reliability is achieved OPC Operationally check the OVERHEAD FLIGHT CREW REST (OFCR)SMOKE DETECTOR SYSTEM using smoke source. 73 Functionally check the Cargo Smoke Detector WATER SEPARATORS. 74 Functionally check the CARGO COMPARTMENT SMOKE DETECTOR HEATERS AND CONTROLLERS FH FH 1 OPC FH FH 1 FNC FH FH 0.75 FNC Operationally check ENGINE FIRE SWITCHES to verify switch and circuit integrity (including Fire Handle unlock solenoid circuitry), and engine isolation AL FH FH 1 OPC Page 26 of 64

27 SYSTEM TASK S/No AMS Task Task Description AMM REF. Zone Access Threshol Repeat MH Task Comments 413AL 414AR AL 416AR Functionally check Engine Fire Extinguishing DISTRIBUTION AL 424AR LINES for blockage and leakage AL 426AR FH FH 2 FNC Operationally check Cargo Fire Extinguishing ARM and DISCHARGE SWITCHES to verify circuitry and Cargo Compartment isolation. Functionally check Cargo Fire Extinguishing System TUBING for evidence of leakage or blockage. Operationally check PRIMARY FLIGHT COMPUTER DISCONNECT SWITCH of Flight Controls Systems AL AL FH FH 1 OPC FH FH 2 FNC FH FH 0.1 OPC Functionally check (off-aircraft) PRIMARY FLIGHT CONTROL SYSTEM HYDRAULIC FUSES - WING- AILERON, WING- FLAPERON, TAIL-RUDDER BL 552HB 552LB 652LB FH FH 3 FNC 81 Operationally check WHEEL JAM BREAKOUT MECHANISM of Flight Controls System. 82 Functionally check PRESSURE REDUCER in RUDDER POWER CONTROL UNITS. 83 Operationally check CONTROL COLUMN BREAKOUT MECHANISM of Flight Controls System. 84 Functionally check COLUMN FORCE TRANSDUCER function of Flight Controls System FH FH 0.4 OPC FH FH 0.3 FNC FH FH 0.3 OPC FH FH 0.3 FNC Functionally check ELEVATOR SURFACE FREEPLAY NOTE: FAA AD # AL 36 MO FH/ 36 MO 2 FNC Functionally check the STABILIZER BALLNUT to BALLSCREW FREEPLAY NOTE : 1)FAA AD )INTERVAL NOTE: For Initial Threshold, whichever occurs later Access :311BL FH/ 18 MO FH/ 60 MO 3.00 FNC Page 27 of 64

28 SYSTEM TASK S/No AMS Task Task Description AMM REF. Zone Access Threshol Repeat MH Task Comments Operationally check ALTERNATE STABILIZER TRIM CONTROL SYSTEM, including verifying no stabilizer motion with single FH FH 0.2 OPC lever operation Operationally check STABILIZER CUTOUT SWITCHES FH FH 0.1 OPC Functionally check STABILIZER TRIM LIMIT SWITCHES FH FH 2.5 FNC 90 Operationally check ALTERNATE CONTROL SWITCHES for HIGH LIFT SYSTEM FH FH 0.3 OPC 91 Operationally check RTO AUTO SPEEDBRAKE function (using thrust lever movement) FH FH 0.3 OPC Operationally check LE SLAT SKEW/LOSS CABLE SYSTEM Note: CMR task # 27-CMR-04* CB 626CB FH FH 1 OPC Operationally check AILERON TRIM INHIBIT FH FH 2 OPC Functionally check RUDDER/RUDDER TAB SURFACE FREEPLAY NOTE: FAA AD # MO FH/ 36 MO 2 FNC Inspect (General Visual) Fuel Surge Tank FLAME ARRESTORS Operationally check the Engine Fuel Spar Valve Battery Circuit Operationally check Engine Fuel SPAR VALVE/ACTUATOR Functionally check APU FUEL SUPPLY LINE and SHROUD. (Pressure decay check.) Operationally check DEFUEL VALVE ACTUATOR BB 642BB / 6000 FC / 6000 FC 1 GVI FH FH 1 OPC FH FH 0.5 OPC FH FH 2 FNC 521DB FH FH 0.5 OPC Functionally check the Center Tank fuel scavenge systems to verify proper operation of both (Left & Right) systems. NOTE: Applicable to airplanes that have incorporated either Service Bulletin (ELMS 1), or Service Bulletin (ELMS 2) FH FH 1 FNC Page 28 of 64

29 SYSTEM TASK S/No AMS Task Task Description AMM REF. Zone Access Threshol Repeat MH Task Comments Functionally check GROSS INTERNAL LEAKAGE of Main (Left, Right, and Center) Hydraulic Systems FH FH 1.5 FNC 212 Note: a) CMR task # 29-CMR-01* Visually check FILTER ELEMENT in each RETURN FILTER MODULE in Main (Left, Right, and Center) Hydraulic Systems. Visually check FILTER ELEMENT in each EDP PRESSURE AND CASE DRAIN FILTER MODULE in Main (Left and Right) Hydraulic Systems. Visually check FILTER ELEMENT in each ACMP PRESSURE AND CASE DRAIN FILTER MODULE in Main (Left, Right, and Center) Hydraulic Systems DL 434CL 434CR 434DR 444CL 444CR 444DR 434CL 434CR 434DR 444CL 444CR 444DR 197DL 434CL 434CR 434DR 444CL 444CR 444DR FH FH 0.7 VCK FH FH 0.5 VCK FH FH 1 VCK Operationally check CENTER HYDRAULIC ISOLATION SYSTEM. Note: a) CMR task # 29-CMR-02* FH FH 2 OPC Clean AIR FILTER for RESERVOIR PRESSURIZATION MODULE in Main (Left, Right, and Center) Hydraulic Systems CL 434CR 444CL 444CR FH FH 2 RST Functionally check the FLIGHT DATA RECORDER system to verify that all required parameters are being recorded. Operationally check UNDERWATER LOCATOR BEACON on Flight Data Recorder. (Use test equipment.) FNC OPC Operationally check AIMS for Coaxial Splitter Unit failures FH FH 0.1 OPC Operationally check INBOARD SELECT SWITCHING FUNCTION. (Use INBOARD DSPL Switches.) FH FH 0.1 OPC Operationally check ALTERNATE DISPLAY CONTROL SWITCHING FUNCTION. (Use DSPL CTRL ALTN Switches.) FH FH 0.1 OPC Operationally check ALTERNATE SOURCE SELECT VALVE for ALTERNATE BRAKE SYSTEM FH FH 0.5 OPC Page 29 of 64

30 SYSTEM TASK S/No AMS Task Task Description AMM REF. Zone Access Threshol Repeat MH Task Comments Operationally check ACCUMULATOR ISOLATION VALVE FH FH 0.2 OPC Functionally check BRAKE ACCUMULATOR bleed-down FH FH 2 FNC Functionally check NORMAL and ALTERNATE BRAKE SYSTEMS AL FH FH 0.5 FNC Inspect (General Visual) the MAIN LANDING GEAR UPLOCK MECHANISM, UPLOCK RELEASE ACTUATOR, ALTERNATE EXTEND POWER PACK, RETRACT ACTUATOR MECHANISM, SIDE BRACE DOWNLOCK MECHANISM and LANDING GEAR DOWNLOCK SPRINGS FC/ 4000 FC/ 0.5 GVI Inspect (General Visual) the MAIN LANDING GEAR DOOR ACTUATOR MECHANISMS, DOOR UPLOCK MECHANISM and DOOR RELEASE/SAFETY VALVE MODULE GVI Inspect (General Visual) the NOSE LANDING GEAR RETRACT ACTUATOR MECHANISM, LOCK MECHANISM, LANDING GEAR DOWNLOCK SPRINGS and UPLOCK RELEASE GVI Inspect (General Visual) the NOSE LANDING GEAR DOOR ACTUATOR, DOOR ACTUATION MECHANISM and DOOR RELEASE/SAFETY VALVE MODULE. Operationally check DOOR LATCH/ACTUATOR and PASSENGER/SUPERNUMERARY OXYGEN SWITCH on Passenger/Supernumerary Oxygen System (without deploying oxygen masks). Operationally check the DOOR LATCH/ACTUATOR AND DECOMPRESSION HORNS in the OFCR GVI 1.5 OPC 0.1 OPC Page 30 of 64

31 SYSTEM TASK S/No AMS Task Task Description AMM REF. Zone Access Threshol Repeat MH Task Comments Operationally check ISOLATION VALVES and CONTROL CABLES CR 0.5 OPC of Potable Water System Functionally check WASTE DRAIN to ensure correct sealing of WASTE DRAIN BALL-VALVE DR 163AL FH FH 1 FNC Restore the Nitrogen Generation System (NGS) Ozone Converter (off-aircraft) PL FH FH 1.5 RST Clean the Nitrogen Generation System (NGS) Primary Heat Exchanger (off-aircraft) QL FH FH 2.5 RST Functionally check the Nitrogen Generation System (NGS) Regenerative Heat Exchanger (off-aircraft) QL FH FH 2.5 FNC Restore the Nitrogen Generation System (NGS) Filter Differential Pressure Sensor Switch (off-aircraft) CR FH FH 1.5 RST Visually check fluid accumulation in the Nitrogen Generation System (NGS) tubing through the drain valve or drain cap LR FH FH 0.5 VCK Inspect (detailed) the Nitrogen Enriched Air (NEA) distribution lines from the Air Separation Module (ASM) to the Fuel Tank Front Spar for damage and leaks. Note: ALI TASK: 47-AWL NR 192PR 192QR 611AB 611CB FH FH 3 DET Restore EPAS and BACKUP BATTERY on all No. 3 over-wing Doors YRS 3 YRS 0.6 RST Page 31 of 64

32 SYSTEM TASK S/No AMS Task Task Description AMM REF. Zone Access Threshol Repeat MH Task Comments Inspect (Detailed) FLIGHT LOCK MECHANISM (including springs) on Passenger Entry Doors DET Inspect (Detailed) FLIGHT LOCK MECHANISM (including springs) on all No. 3 over-wing Doors. Inspect (Detailed) GIRT BAR MECHANISM INTERLOCK on Passenger Entry Doors. Inspect (Detailed) LATCH TORQUE TUBE INTERLOCK on all No. 3 Over-wing Doors Inspect (Detailed) EPAS TUBING on all Passenger Entry Doors Inspect (Detailed) EPAS TUBING on all No. 3 Over-wing doors DET 1 DET 0.25 DET 1875 DY 1875 DY 2 DET 1875 DY 1875 DY 0.5 DET Functionally check EPAS CIRCUITRY including THE EPAS SQUIB, MODE SELECT SWITCH, and DOOR OPEN SWITCH on all Passenger Entry Doors to verify correct electrical continuity and isolation FNC Functionally check the following Passenger Entry Door mechanisms: LATCH, HINGE, HANDLE, VENT DOOR, MODE SELECT, GIRT BAR, HOLD OPEN, including EPAS ACTUATOR and SNUBBER. Functionally check the following mechanisms on all No. 3 Overwing Doors : LATCH, HINGE, HANDLE, VENT DOOR, MODE SELECT, HOLD OPEN, PROGRAMMING CHAIN, including EPAS ACTUATOR and SNUBBER FNC 0.5 FNC Operationally check MANUAL DRIVE MECHANISM and LIFT POWER DRIVE UNIT BRAKE on the Forward Large Cargo Door OPC Page 32 of 64