Over-Serviceable-Limit Extensions [CFMI]

TASK 72-00-00-200-005-A
Over-Serviceable-Limit Extensions

1. Reason for the Job
It can occur that specific defects do not agree with the "Maximum Serviceable Limits", and that the maintenance facilities, at a given location, are not sufficient to do the necessary corrective actions.
In these circumstances, limit extensions will permit to send the engine where correction is possible, or to schedule the necessary maintenance in the extension period.

NOTE: The limit extensions are one-time extensions only. Applicable hardware action is necessary at the completion of the extended serviceable period.

2. Job Set-up Information
A. Referenced Information

REFERENCE	DESIGNATION
TASK 72-21-00-210-002-A	Inspect Fan Rotor Blades Removed from the Fan Disk
TASK 72-21-00-210-025-A	Inspect Fan Rotor Blades Installed on the Fan Disk
TASK 72-23-00-210-003-A	Detailed Inspection of Spinner, Engine Inlet, Fan Blades, Fan Outlet and Abradable Material
ESM 722101200000
Extended Booster Rotor Blades Damage Limits (all 3 blade stages)
Extended Vanes Damage Limits (stage 1 vane assy only)
Combustion Chamber Inspection

3. Job Set-up
Subtask 72-00-00-941-054-A ** ON A/C NOT FOR ALL

A. Not applicable

4. Procedure
Subtask 72-00-00-210-052-A ** ON A/C NOT FOR ALL

A. Over-Serviceable-Limit Extensions

CONDITION	MAX. EXTENSION
1.Fan and booster
A.Spinner front cone
(1)Damaged surface protection greater than 50 percent of total surface	50 cycles
B.Damper
(1)Upper shield metal debonding or missing	10 cycles/25 hours
C.Fan blade
(1)Fully missing molydag on inner faces of the platforms	250 cycles
(2)Flaking of Cu.Ni.In coating on blade dovetail pressure faces (contact areas), less than 10 percent and if there is no indication of wear on base material	Examine blades for serviceability (Ref. AMM TASK 72-21-00-210-002) 1200 cycles after relubrication. Repeat extension is permitted
(3)Flaking of Cu.Ni.In coating on blade dovetail pressure faces (contact areas), more than 10 percent and less than 50 percent if there is no indication of wear on base material	400 cycles after relubrication. Repeat extension is not permitted
(4)Shingling at mid span shrouds	Turn the shingled blades to the 12 o'clock position and unshingle with hand force or by using a piece of wood. Examine blades for serviceability (Ref. AMM TASK 72-21-00-210-025). Remove and send the shingled blades to a shop for a dimensional and an F.P.I. inspection in less than 50 cycles ( ESM 722101200000).
(5)Nicks, dents, scratches and sheared edges on mid-span shroud surfaces less than 0.035 in. (0.9 mm) deep if defects are not in the mid-span shroud to airfoil fillet radius	50 cycles
(6)Missing or damaged hard coating on mid span shroud pressure faces more than 10 percent but less than 40 percent of coated area	50 cycles
D.Shim (POST CFM SB 72-0621)
(1)Missing molydag coating exceeding 25 percent on pressure face	250 cycles
E.Fan disk
(1)Wear greater than 50 percent of area on disk dovetail pressure faces	100 cycles
F.Booster rotor blade (all 3 blade stages) for: Extended Booster Rotor Blades Damage Limits (all 3 blade stages) ** ON A/C NOT FOR ALL
(1)Piece missing:
any number in area G, at L/E and T/E tip corners, 0.787 in. (20 mm) radial and 0.492 in. (12.5 mm) axial	50 cycles/75 hours
(2)Cracks and tears in area G, 0.787 in. (20 mm) from tip : any number less than 0.787 in. (20 mm) radial and less than 0.492 in. (12.5 mm) axial	50 cycles/75 hours
(3)Wear or local distortion of T/E and L/E tips if less than 15 blades, 0.984 in. (25 mm) radial and 0.59 in. (15 mm) axial	100 cycles/150 hours
(4)Nicks, dents, scratches for area E: any number, less than 0.059 in. (1.5 mm) in diameter, protrusion acceptable, not thru	50 cycles/75 hours
(5)Nicks, dents, scratches for airfoil out of area E, not L/E and T/E: any number, less than 0.236 in. (6 mm) in diameter, protrusion acceptable	50 cycles/75 hours
(6)Nicks, dents, scratches out of area E on L/E and T/E: maximum axial length less than 0.059 in. (1.5 mm)	50 cycles/75 hours
(7)Distorted L/E and T/E, out of area E maximum circumference equals 0.275 in. (7 mm) radial length equals 0.708 in. (18 mm)	50 cycles/75 hours
G.Booster vanes (stage 1 vane assy only) for: Extended Vanes Damage Limits (stage 1 vane assy only) ** ON A/C NOT FOR ALL
(1)Piece missing: maximum 20 blades more than 0.256 in. (6.5 mm) axial, 0.728 in. (18.5 mm) radial, no cracks starting from damage area allowed in areas A and B	50 cycles/75 hours
(2)Cracks and tears in area C: any number, more than 0.256 in. (6.5 mm) radial and 0.078 in. (2 mm) axial. In areas A and B, any number more than 0.128 in. (3.25 mm) radial and 0.039 in. (1 mm) axial	10 cycles/15 hours
(3)Distortion of T/E and L/E: any number if the length L is not more than 1 in. (25.4 mm) and the maximum dimension X along the chord width is not more than 0.492 in. (12.5 mm)	50 cycles/75 hours
(4)Nicks, dents, scratches for areas A and B: any number, less than 0.157 in. (4 mm) in diameter, protrusion acceptable	10 cycles/15 hours
(5)Nicks, dents, scratches for area C: any number, less than 0.295 in. (7.5 mm) in diameter, protrusion acceptable	50 cycles/75 hours
(6)Nicks, dents, scratches L/E and T/E maximum axial length less than 0.118 in. (3 mm) in diameter	20 cycles/30 hours
2.Fan frame
A.Fan frame case
(1)Cracks, any number if max. length of 0.16 in. (4.06 mm) and min. separation of 1 in. (25.4 mm)	10 cycles or 25 hours
(2)Nicks and dents: any number	10 cycles or 25 hours
B.Fan inlet case
(1)Cracks: any number, if max. length of 0.16 in. (4.06 mm) and min. separation of 1 in. (25.4 mm)	10 cycles or 25 hours
(2)Nicks and scratches: any number	10 cycles or 25 hours
(3)Crater in abradable liner (length<5x width) and damage other than crack rub and circumferential defect: If the damage is within the maximum serviceable limits, (Ref. AMM TASK 72-23-00-210-003) but the fan case parent metal is exposed and is confirmed via visual inspection to be undamaged.	50 cycles or 125 hours
(4)Grooves in abradable liner (orientated within 0 deg. to 80 deg. from engine axis and length>5x width: If the damage is within the maximum serviceable limits, (Ref. AMM TASK 72-23-00-210-003) but the fan case parent metal is exposed and is confirmed via visual inspection to be undamaged.	50 cycles or 125 hours
(5)Circumferential defect in abradable liner (360 deg. or orientated within 80 deg. to 90 deg. from engine axis): for one or a cumulated defect less than 2 in. (50.8 mm) if the fan case parent metal remains not damaged under visual inspection.	50 cycles or 125 hours
C.Aluminium Outlet guide vanes (OGV)
(1)Vane missing, broken vane maximum number = 2, provided that at least 10 vanes are in between	10 cycles or 25 hours
(2)Nicks, dents or scratches: any amount	10 cycles or 25 hours
(3)Eroded protective coating: any amount	100 cycles or 100 hours
D.Composite Outlet guide vanes (OGV)
(1)Metal Leading edge missing allowed if missing material is over 0.78 in. (20 mm) height and 0.39 in. (10 mm) wide. Speed tape (CP2516) usage is recommended when missing metal on leading edge to preserve repair possibility, avoiding any damage on composite material.	100 cycles
E.OGV inner seal
(1)Cracks, cut or torn seal at mating with OGV: any amount	25 cycles or 50 hours
F.OGV outer fairing
(1)Missing OGV outer fairing: Maximum number = 5	100 cycles or 100 hours
G.Composite outlet guide vanes (OGV)
(1)Vane missing, broken vane: maximum number = 2, provided that at least 10 vanes are in between	10 cycles or 25 hours
(2)Cracks or tears on airfoil	50 cycles
(3)Nicks, dents on airfoil or T/E	100 cycles
(4)Nicks, dents on L/E: less than 0.32 in. (8.12 mm) deep cumulative length less than 0.59 in. (15 mm) above limit	100 cycles with speed tape applied 50 cycles
(5)Delamination (separated layers) or split fibers on airfoil or T/E	50 cycles
(6)Delamination (separated layers) or split fibers on L/E	100 cycles with speed tape applied
(7)Radial separation between L/E polyurethane and airfoil ( 0.39 in. (10 mm) from L/E) any length, any amount, max. number = 10 vanes	500 cycles
(8)Missing protective coating any amount (100 percent airfoil surface)	500 cycles
H.Fan duct panel
(1)All damaged beyond 72-23-00 criteria; not serviceable	50 cycles with 2 missing louvers maximum
(2)One fan duct panel missing is permitted, if you make sure that the VBV area is free of unwanted object before the first aircraft release of the day.	10 cycles
J.Splitter fairing
(1)Cracks: any amount	10 cycles or 25 hours
3.Compressor rotor
A.Compressor rotor blades NOTE: The depth of a defect such as a nick is measured along the axis of the damage unless otherwise noted.
(1)Stages 1-4 radial cracks within 0.30 in. (7.6 mm) of the leading and trailing edges more than 0.25 in. (6.4 mm) but less than 0.40 in. (10.2 mm) in length.	10 cycles or 25 hours
(2)Stages 1-4 chord-wise cracks more than 0.20 in. (5.1 mm) but less than 0.30 in. (7.6 mm) in length.	10 cycles or 25 hours
(3)Stages 1-4 nicks, missing material and erosion on the leading and trailing edges found in Dim. B more than 0.04 in. (1.0 mm) but less than 0.08 in. (2.0 mm).	10 cycles or 25 hours
(4)Stages 1-4 dents on the leading and trailing edges found in Dim. B more than 0.04 in. (1.0 mm) but less than 0.08 in. (2.0 mm) in depth, and less than 0.06 in. (1.5 mm) deflection from the original contour.	10 cycles or 25 hours
(5)Stages 1-4 nicks, dents and tears on the leading and trailing edge in Dim. A more than 0.25 in. (6.4 mm) but less than 0.30 in. (7.6 mm) in depth.	10 cycles or 25 hours
(6)Stage 1 missing material and erosion at the leading and trailing edge tip corners more than 0.30 in. (7.6 mm) but less than 0.40 in. (10.1 mm) in depth.	10 cycles or 25 hours
(7)Stage 2, more than 4 blades missing material and erosion at the leading and trailing edge tip corners more than 0.30 in (7.6 mm) but less than 0.40 in. (10.2 mm) in depth.	10 cycles or 25 hours
(8)Stage 3, more than 5 blades missing material and erosion at the leading and trailing edge tip corners more than 0.30 in (7.6 mm) but less than 0.40 in. (10.2 mm) in depth.	10 cycles or 25 hours
(9)Stage 4, more than 6 blades missing material and erosion at the leading and trailing edge tip corners more than 0.30 in (7.6 mm) but less than 0.40 in. (10.2 mm) in depth.	10 cycles or 25 hours
(10)Stages 1-4 nicks, dents and missing material on the leading and trailing edges of the lower 25% of the airfoil (but not the root radius) more than 0.03 in. (0.76 mm) but less than 0.08 in. (2.0 mm).	10 cycles or 25 hours
(11)Nicks, dents, wear and scratches of the trailing edge root radius of stage 2 and stage 3 of more than 0.03 in. (0.8 mm) but less than 0.08 in. (2.0 mm).	10 cycles or 25 hours
(12)Stages 5-9 radial cracks that are not more than 0.20 in. (5.1 mm) from the leading or trailing edge and more than 0.15 in. (3.8 mm) but less than 0.20 in. (5.1 mm) in length.	10 cycles or 25 hours
(13)Stages 5-9 chord-wise cracks that are not more than 0.20 in. (5.1 mm) from the tip and are more than 0.15 in. (3.8 mm) but less than 0.20 in. (5.1 mm) in length.	10 cycles or 25 hours
(14)Stages 5-9 nicks, tears, missing material and erosion on the leading and trailing edges found in Dim. B that are more than 0.04 in. (1.0 mm) but less than 0.08 in. (2.0 mm).	10 cycles or 25 hours
(15)Stages 5-9 dents on the leading and trailing edges found in Dim. B that are more than 0.04 in. (1.0 mm) but less than 0.08 in. (2.0 mm) in depth and less than 0.06 in. (1.5 mm) deflection from the original contour.	10 cycles or 25 hours
(16)Stages 5-9 nicks, dents and tears on the leading and trailing edges found in Dim. A that are more than 0.15 in. (3.8 mm) but less than 0.20 in. (5.1 mm).	10 cycles or 25 hours
(17)Stages 5-9 missing material and erosion at the leading and trailing edge tip corners if the damage is more than 0.20 in. (5.1 mm) but less than 0.30 in. (7.6 mm)	10 cycles or 25 hours
(18)Stages 5-9 curl on the end of the airfoil when the blade chord is more than 50% but less than 75% of the chord maximum radial length, 0.30 in. (7.6 mm), when it does not engage the stationary parts during operation.	10 cycles or 25 hours
(19)Stages 6-9 nicks, dents and missing material on the leading and trailing edges found in the lower 25% of airfoil (but not the root radius) more than 0.03 in. (0.76 mm) but less than 0.08 in. (2.0 mm).	10 cycles or 25 hours
(20)Stage 5 nicks, dents and missing material on the leading and trailing edge found in the lower 25% of the airfoil (but not the root radius) more than 0.02 in. (0.51 mm) but less than 0.08 in. (2.0 mm) in depth.	10 cycles or 25 hours
(21)Two blade locks in the same stage with any number of cracks if no blade locks are loose on that stage	10 cycles or 25 hours
(22)One loose blade lock in a stage if the other blade lock on the same stage is not loose or cracked	10 cycles or 25 hours
B.Compressor rotor blade locks
(1)Two cracked blade locks	10 cycles or 25 hours
(2)One loose blade lock	25 cycles or 100 hours
4.Compressor front stator
A.Casing cracks 0.17 in. (4.32 mm) max. length in skin	10 cycles or 25 hours
B.Casing nicks, pits, scores or scratches, any amount, any depth	10 cycles or 25 hours
C.Broken actuation ring connector, one side only, if connector is replaced	5 cycles
D.Vane actuation ring cracks, distortion, bends, twists or distress, provided ring has not separated	5 cycles
E.Loose vane assemblies with metal-to-metal contact on up to 50 percent of vanes	10 cycles or 25 hours
5.Combustion case
A.Forward and aft flange radial cracks inward from bolt holes	10 cycles
B.Midflange radial cracks	10 cycles
C.Maximum of 10 broken midflange bolts with no more than 4 broken bolts in any group of 20	25 cycles
D.High pressure turbine (HPT) shroud cooling and compressor discharge pressure (CDP) pad cracks longer than 0.06 in. (1.52 mm) from bolt holes	10 cycles
6.Combustion chamber
A.Dome assembly
(1)Radial crack in spectacle plate	25 hours
Any number up to 2.5 inches (63.5 mm) in length and not connected to each other.
(2)Circumferential crack in spectacle plate	25 hours
Any number up to 3.6 inches (91 mm) in length separated by 4.8 inches (125 mm)
(3)Connected cracks in spectacle plate	25 hours
Not more than one radial crack 2.5 in. (50.8 mm) long with one circumferential crack 3.6 in. (91 mm) long, separated by 4.8 in. (125 mm).
(4)Missing material from spectacle plate	25 hours
The damage is more then the given limits.
(5)Radial crack in deflector or sleeve	25 cycles
Any number up to 0.6 in. (16 mm) in length.
(6)Circumferential cracks in deflector or sleeve	25 cycles
Any number up to 0.9 in. (23mm) in length.
(7)Connected cracks in deflector or sleeve	25 cycles
Connection of any radial and circumferential cracks within limits of (5) and (6) above. Limit is exceeded when third crack connects.
(8)Missing material from extensions on deflector if:	100 cycles
The exposed cooling holes are within pattern restriction shown in view ZZ, sheet 2 of the figure Combustion Chamber Inspection ** ON A/C NOT FOR ALL
(9)Missing material from extensions on sleeve	50 cycles
Any amount up to 0.24 in. (6.1 mm) maximum depth.
(10)Burn through holes	25 cycles
3 per dome 1.2 in. (30mm) x 1.2 in. (30 mm) maximum
B.Inner and outer liners
(1)Outer liner axial cracks	100 cycles
Up to 5 cracks across more than one panel, and a crack can go across up to 5 panels in sequence
(2)Outer liner axial cracks (from outer side borescope)	25 cycles
Up to 5 cracks across more than one panel, and a crack can go across up to 5 panels. At least one of the cooling ribs (3, 4, 5, or 6) does not have cracks that extend through to the outer side. Rib 1 is not cracked through.
(3)Inner liner axial cracks	100 cycles
Up to 5 cracks across more than one panel, and a crack can go across up to 4 panels in sequence.
(4)Circumferential cracks	25 cycles
Any number up to 3 dilution lands in length separated by 3 non-cracked dilution lands.
(5)Connected cracks	100 cycles
Connection of any axial and circumferential cracks up to max.limits of paragraphs (1), (2), (3), and (4).
(6)Burn through or missing material
For each liner: For each liner, there are not more than 3 holes in adjacent panels that are axially aligned. The maximum size of any hole is less than 6 times the size of a dilution hole. The total area of burn through is less than 24 times the size of a dilution hole.	Repeat BSI every 250 cycles
(7)Burn through or missing material
For each liner: For each liner, there are more than 3 holes in adjacent panels that are axially aligned. The maximum size of any hole is greater than 6 times the size of a dilution hole. The total area of burn through exceeds 24 times the size of a dilution hole.	100 cycles
(8)Missing overhangs	25 cycles
Per liner: 17 areas each twice the size of a dilution hole, providing max. axial alignment of distress is 3 adjacent panels
(9)Distortion	25 cycles
Any amount within 0.7 in. (17.78 mm) of original contour
7.Fuel Nozzles
A.Fuel nozzles with dislodged wear sleeves or wear sleeves with 4 interrupted weld designs.	5 cycles
8.HPT nozzle
A.Leading edge missing material, up to row 1 or up to 0.2 in. (5.1 mm) beyond row 11	10 cycles
B.Concave surfaces of airfoil missing material, from cracking or burn-through, up to 0.75 in. (19.04 mm) diameter per vane	25 cycles
C.Convex side missing panel	25 cycles provided HPT blades are within limits
D.Inner and outer platforms missing material, from cracking or burn-through, up to 0.5 in. (12.7 mm) diameter per segment	25 cycles
E.Trailing edge missing material up to 0.75 in. (19 mm) in axial direction	25 cycles
F.Baffle missing material, any amount	10 cycles
9.HPT rotor blade
A.Trailing edge cracks in Area A less than 0.2 in. (5.1 mm) long	10 cycles
B.Trailing edge cracks in Area B less than 0.24 in. (6 mm) long. Do borescope inspection again every 30 cycles (max.)	120 cycles
C.Trailing edge cracks in Area C less than 0.15 in. (3.8 mm) long	10 cycles
D.Radial tip cracks less than 0.35 in. (8.9 mm) long	10 cycles
E.Leading edge cracks in Area A less than 0.1 in. (2.54 mm) long	10 cycles
F.Axial nose or gill hole cracks in Area B less than 0.05 in. (1.27 mm) long	10 cycles
G.Radial nose or gill hole cracks in Area B less than 0.06 in. (1.52 mm) long	10 cycles
H.Radial nose or gill hole cracks in Area C less than 0.03 in. (0.76 mm) long	10 cycles
J.Axial cracks in concave airfoil area within 0.7 in. (17.78 mm) of trailing edge and above 7th T.E. slot from platform: any amount 0.35 in. (8.9 mm) maximum length, if they do not connect with trailing edge slot	10 cycles
K.Leading edge missing material in areas A and B. Any amount provided cavity 2 is not exposed (any number of blades)	25 cycles
L.Missing trailing edge material more than 0.50 in. (12.7000 mm) axially but less than 0.60 in. (15.2400 mm) axially or to the bottom of the 6th trailing edge slot.	30 cycles
10.HPT shroud and stage 1 low pressure turbine (LPT) nozzle
A.HPT shrouds
(1)- Cracks: any amount not connecting and across width of shroud	10 cycles
(2)- Burn through of shroud rub land	25 cycles
B.Stage 1 LPT nozzle
(1)Axial cracks in all areas: up to 1 in. (25.4 mm) long if not more than 2 adjacent airfoils for each segment	10 cycles
(2)Radial cracks on convex side: one for each airfoil up to 1.2 in. (30,5 mm) long and no axial crack on the same side of the airfoil	10 cycles
(3)Burns, erosion, corrosion and missing metal up to 1 sq. in. (645.16 sq. mm) per airfoil and no cracks extending from distressed area	5 cycles
11.LPT Rotor
A.LPT blades (all stages) for: Measurements of Airfoil Indication on Low Pressure Turbine Blades (all stages)
(1)Blade pretwist
Total gap, for stage 1, up to 0.1 in. (2.54 mm)	5 cycles
Stage 2-4 gaps such that adjacent interlocks, do not contact each other	5 cycles
(2)0.08 in. (2.03 mm) max. deflection over a length 10 times longer max., only for stage 1 LPT blades distorted leading edges, due to overtemperature	15 cycles
(3)Stage 1, 2, 3 blades
Area E: Any amount of impact damage provided there is no missing material or cracks	5 cycles or 10 hours
Other areas: Any amount of impact damage such as bending, nicks and/or dents is allowed provided there is no missing material or cracks exceeding 50 percent of chord width	5 cycles or 10 hours
(4)Stage 4 blades
Any amount of tip shroud interlock wear allowed	25 cycles or 50 hours
(5)Stage 4 blades
Blades tip shroud protrusion not to exceed 0.04 in. (1 mm)	10 cycles or 25 hours
(6)Stage 4 blades
Area E:
Any amount of impact damage such as nicks and/or dents is allowed provided there is no missing material or cracks	5 cycles or 10 hours
Other areas:
Any amount of impact damage. One complete airfoil and any number of tip shrouds with associated airfoil tips may be missing provided engine vibration is not excessive	5 cycles or 10 hours
(7)Stage 4 blades
Blade tip shrouds shingled or unlatched provided rotor turns freely and engine vibration is not excessive	5 cycles or 10 hours in shingled condition
B.Nozzle segments
(1)Cracks 0.5 in. (12.7 mm) long each, 2 per vane, total length of 1 in. (25.4 mm)	10 cycles
(2)Nicks, dents, tears, missing pieces up to 2 sq. in. (1290.32 sq. mm) on nonadjacent vanes provided there are no cracks extending from distressed areas	10 cycles
C.Stage 4 shroud abradable material
(1)Worn, jagged or crushed sealing surface exceeding 50 percent of the honeycomb height provided sectors of the shroud abradable material are not missing	10 cycles
12.LPT Casing
A.Forward and aft flanges
(1)One crack connecting 2 bolt holes without penetrating pressure vessel outer skin	10 cycles
(2)One crack into skin 0.4 in. (10.16 mm) long maximum	10 cycles
B.External surface of the casing
(1)One crack 0.4 in. (10.16 mm) long maximum	10 cycles
C.Cooling air tube and manifold assemblies	10 cycles
(1)One separated circumferential tube
(2)3 in. (76.2 mm) cumulative cooling air manifold crack
(3)One separated cooling air tube support
D.Thread ports and bosses
(1)One crack 0.5 in. (12.7 mm) maximum providing there is no leakage	10 cycles
13.Turbine frame
A.Forward and aft flanges	10 cycles
(1)One circumferential crack connecting two bolt holes
(2)One crack into skin 0.5 in. (12.7 mm) maximum
B.Engine mounting lug areas airframe attach points only	10 cycles
(1)One crack out of one mount lug bolt hole 0.25 in. (6.35 mm) maximum
(2)Skin crack 0.25 in. (6.35 mm) maximum
C.Threaded parts and bosses	10 cycles
(1)One crack 0.5 in. (12.7 mm) long providing there is no fluid or air leakage
D.Stud on the aft face of the inner hub
(1)Missing/broken/loose stud(s):
One (1) or two (2) studs:	500 cycles/500 hours
Three (3) studs:
*If not adjacent to each other:	500 cycles/500 hours
*If two (2) non-serviceable studs are adjacent, but the third one is separated from them by two (2) serviceable studs:	500 cycles/500 hours
*If not:	Replace studs
Four (4) studs or more:	Replace studs
E.Thermal insulation blankets	100 cycles
(1)Missing or protruding blankets
F.Outer casing skin areas connecting with struts, except mounting lug areas
Cumulative length for each strut area
(1)For struts 5 to 12 less than 7 in. (177.8 mm)	50 cycles
(2)For struts 2, 4, 13, 15, 16 less than 3.5 in. (88.5 mm)	50 cycles
(3)Missing or protruding blankets
G.Other areas	10 cycles
(1)One crack 0.25 in. (6.35 mm) maximum
14.Accessory gearbox
A.Two opposite keylock studs missing provided there is no leakage at flange	3 cycles or 30 hours
B.Oil leakage from AGB/Starter carbon seal	10 cycles provided seal drain line is disconnected and drain cavity is capped

[Rev.10 from 2021] 2026.04.01 12:54:42 UTC