FOR REFERENCE ONLY B727 CONTINUATION TRAINING

Transcription

1 B727 CONTINUATION TRAINING Q1 & Q2 2016

2 Contents: 1 Introduction 2 ADs 3 Maintenance Related MOR

3 1 Introduction With the introduction of the 727 type to Altitude Globals approval, this is the first CBT module for this type. Where it is not possible to surmise the history of the type, this training issue covers the preceding 2 years as opposed to the usual 6 months. Future editions will resume the usual 6 monthly on the bi annual basis. The approval being made active is reflected in MOE Part 1.9 as follows: Aircraft Type / Station Location Listing See note Leipzig (LEJ) Bergamo (BGY) Ancona (AOI) Venice (VCE) Brussels-DHL (BRU) Leige (LGG) Bahrain (BAH) Basel (BSL) Oslo (OSL) Stansted (STN) Athens (ATH) Malta (MLA) Malpensa (MXP) Brussels-non-DHL (BRU) Doncaster (DSA) B737-3/4/500 (CFM56) B757-2/300 (RB211 & PW2000) B767-2/300 (GE CF6) B (PW4000 & GE CF6) B (PW JT8D) A300-B4 (GE CF6) A (PW4000) A319/20/21 (CFM56 & V2500) B777-2/3(PW4000/GE90/Trent 800) Aircraft type listed in the table above includes passenger & freighter variants. The scope of work includes the APU relevant to the aircraft type within the scope permissible under the A1 rating. A shaded cell denotes a passive approval and as such is subject to the requirements of Technical Procedure 14 for monitoring and re-activation. Note that the Doncaster line station approval for B727 has now ceased and will be reflected in the next MOE revision.

4 2 B727 Airworthiness Directive Listing This is the first Altitude Global Listings for Airworthiness Directives and therefore include all AD s listed since beginning of There are many more preceding these and there exclusion from this CBT does not devalue or imply any validity. Please review further AD s on the EASA website. It is also of note that 2 recent AD s listed are for modified 727 Rolls Royce Tay engine aircraft, and although rare worthy of noting. EASA AD US ATA 53 Applicability: Limit of validity (LOV) - cracking in stringers or frames series airplanes This AD is intended to complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. For certain airplanes, this AD requires repetitive inspections for cracking in stringers or frames until modification, and repair if necessary. We are issuing this AD to detect and correct cracking in stringers or frames originating at or near stringer-to-frame attachment fastener holes, which could result in reduced structural integrity of the airplane, and decompression of the cabin.

5 EASA AD US ATA 35 Replacing the low-pressure oxygen hoses Applicability: 727, 727C, , C, , and F This AD was prompted by a report of a fire that originated near the first officer's area and caused extensive damage to the flight deck on a different airplane model. This AD requires replacing the low-pressure oxygen hoses with non-conductive low-pressure oxygen hoses in the flight compartment. We are issuing this AD to prevent electrical current from inadvertently passing through an internal, anti-collapse spring of the lowpressure oxygen hose, which can cause the low-pressure oxygen hose to melt or burn, leading to an oxygen-fed fire and/or smoke in the flight deck. EASA AD US ATA 57 Applicability: Repetitive inspection intervals for the inboard and outboard carriage attach fittings for the outboard foreflaps 727, 727C, , C, , and F series airplanes AD required repetitive inspections of the carriage attach fittings on the inboard and outboard foreflaps of each wing for cracking and other discrepancies, and corrective actions if necessary. This new AD requires reducing certain repetitive inspection intervals for the inboard and outboard carriage attach fittings for the outboard foreflaps, requires previously optional terminating actions which install improved outboard foreflap carriage attach fittings, and adds new initial and repetitive inspections of those fittings and corrective actions if necessary. This AD was prompted by a report of broken inboard and outboard carriage attach fittings of the outboard foreflaps found during an inspection. We are issuing this AD to detect and correct fatigue cracking of the attach fittings of the foreflap carriage of the wings, which could result in partial or complete loss of the foreflap and consequent loss of controllability of the airplane.

6 AD No.: R1 ATA 72 Engine Stages 2 and 3 Low Pressure Turbine Discs Inspection / Replacement ROLLS-ROYCE DEUTSCHLAND Ltd & Co KG Applicability: Tay and Tay engines Strip-down of some Tay engines revealed excessively corroded stage 2 and stage 3 LPT discs. Subsequent evaluation concluded that the corrosion was caused by the environment in which these engines had been operated. This condition, if not detected and corrected, could lead to an uncontained LPT disc failure, potentially resulting in damage to, and/or reduced control of the aeroplane. To address this unsafe condition, Rolls-Royce Deutschland Ltd & Co KG (RRD) issued Alert Non-Modification Service Bulletin (NMSB) TAY-72-A1524 to provide inspection instructions for stage 2 and stage 3 LPT discs. Consequently, EASA issued AD to require repetitive inspections of stage 2 and stage 3 LPT discs on certain engines. That AD was superseded by EASA AD (later revised), which was subsequently superseded by EASA AD , in both cases to expand the population of affected engines. After EASA AD was issued, it was identified that stage 2 and stage 3 LPT discs corrosion may also affect engines, which were operated in such an environment in the past. For the reasons described above, EASA issued AD , retaining the requirements of EASA AD , which was superseded, and expanded the AD applicability to include engines, which were previously operated under these specific environmental conditions. After that AD was issued, RRD issued Revision 6 of NMSB TAY-72-A1524 introducing a clarification about the counting of the service life accumulated by the stage 2 and stage 3 LPT discs relevant for accomplishment of inspection required by that NMSB. This AD is revised to introduce the new compliance time relevant for accomplishment of the inspection required by this AD.

7 AD No.: ATA 72 Applicability: Engine High Pressure Turbine Stage 1 Disc Cyclic Life Limit Reduction ROLLS-ROYCE DEUTSCHLAND Ltd & Co KG Tay 650 and Tay 651 engines A recent analysis identified the need to reduce the existing cyclic life limit of certain High Pressure Turbine (HPT) Stage 1 discs, Part Number (P/N) JR32013, as compared with the values published in RRD Tay 650 and Tay 651 engine Time Limit Manuals (TLM), Chapter Operation of the affected HPT Stage 1 disc P/N JR32013 beyond the reduced cyclic life limit would likely result in an unsafe condition. This condition, if not corrected, could lead to part failure, possibly resulting in release of high energy debris with consequent damage to the aeroplane and/or injury to the occupants. Prompted by the analysis results, RRD issued Alert Non Modification Service Bulletin (NMSB) TAY-72-A1821 to inform about the reduced cyclic life limits for various affected flight plans. For the reasons described above, this AD requires implementation of the reduced cyclic life limits, as applicable to the various flight plans and replacement of HPT Stage 1 disc P/N JR32013 that have already exceeded the reduced cyclic life limit.

8 AD ATA 28 Repetitive inspections of the in-tank fuel boost pump wiring, installation Applicability: 727, 727C, , C, , and F We are superseding Airworthiness Directive (AD) for all The Company Model 727 airplanes. AD required repetitive inspections of the in-tank fuel boost pump wiring, installation of sleeving over the in-tank fuel boost pump wires, repetitive inspections of a certain electrical wire, sleeve, and conduit, and applicable investigative and corrective actions; and repetitive engine fuel suction feed operational tests. This new AD also requires replacement of the wire bundles for the wing and center fuel boost pumps, installation of convoluted liners, and related investigative and corrective actions if necessary. This new AD also requires replacement of the fuel quantity indicating system (FQIS) wires, a lowfrequency eddy current inspection for cracking, and repair if necessary. This new AD also requires revising the maintenance program to incorporate changes to the airworthiness limitations section. This AD was prompted by a report of damage found to the sleeve, jacket, and insulation on an electrical wire during a repetitive inspection. We are issuing this AD to prevent chafing of the fuel boost pump electrical wiring and leakage of fuel into the conduit, and to prevent electrical arcing between the wiring and the surrounding conduit, which could result in arc-through of the conduit, and consequent fire or explosion of the fuel tank.

9 AD ATA 53 Inspection for cracks in the main wheel well pressure floor Applicability: 727, 727C, , C, , and F We are adopting a new airworthiness directive (AD) for certain The Company Model 727 airplanes. This AD was prompted by certain mandated programs intended to support the airplane reaching its limit of validity of the engineering data that support the established structural maintenance program. This AD requires an inspection for cracks in the main wheel well pressure floor and a preventive modification or permanent repair, as applicable. We are issuing this AD to prevent cracking in the main wheel well pressure floor, which could result in reduced structural integrity of the airplane, and decompression of the cabin. AD ATA 57 Limit of validity (LOV) - cracking of small repairs done on the vertical flange of the rib chord Applicability: 727, 727C, , C, , and F We are adopting a new airworthiness directive (AD) for all The Company Model 727 airplanes. This AD will complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. This AD requires repetitive inspections for cracking of small repairs done on the vertical flange of the rib chord, repetitive inspections for cracking along the upper fillet radius of the rib chord, and a large repair or preventive modification if necessary. Accomplishment of a large repair or preventive modification terminates the actions of this AD. We are issuing this AD to prevent cracks in the rib upper chord, which could result in the inability of the wing structure to support the limit load condition, and consequent loss of structural integrity of the wing.

10 3. Maintenance Related MOR The following are maintenance related MOR from the UK CAA MOR digest. As the information is protected and strictly controlled by the UK CAA, it is respectfully requested that this information is not circulated. No part of the MOR publication may be reproduced or transmitted outside of the organisation without the express permission in writing of the Civil Aviation Authority Safety Data Office. 727 Loss of nozzle extension from a spray boom during testing. A test flight was performed in accordance with an approved flight test plan to investigate an oil-spill, spray-dispersant system. After landing, it was found that six small spray nozzle extension tubes had sheared off. The nozzle extensions were fine tubes of stainless steel with approximate dimensions of 10 cm long and cm in diameter. The aircraft had previously flown in the same test configuration with no similar occurrence. However, this was the first time that this new system had been used to release fluid. This flight was conducted under flight test permit conditions under DOA EASA 21J.321 control. Aircraft has been quarantined pending DOA inspection and will not be released into service until appropriate assessment and corrective action has been completed. - END -