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Pilot`s Notes Wellington Pilot`s Notes

WELLINGTON III, X, XI, XII, XIII AND XIV

PILOT'S NOTES

January 1944.

OPERATING DATA

54. Engine Data: Hercules XI (Mk. III aircraft only)

(i) Fuel.—100 octane. (The reduced limitations for use with 87 octane fuel are shown in brackets.)

(U) Oil.—Sec A.P.1464/C37.

(iii) Engine limitations:

  R.p.m. Boost lb/sq.in. Temp. Cyl °C Oil inlet
MAX. TAKE-OFF TO 1,000 FT. M 2,800 +6¾(+5) - -
MAX. CLIMBING M
HR LIMIT S
2,500 (2,400) +3½;(+2½) 270 90
MAX. RICH M
CONTINOUS S
2,500 (2,400) +3½;(+2½) 270 80
MAX. WEAK M
CONTINOUS S
2,500 (2,200) zero 270 80
COMBAT M
5MINS. LIMIT S
2,800 +6¾(+5) 280 100
OIL PRESSURE
NORMAL
.. .. .. 80 lb/sq.in
MINIMUM .. .. .. 70 lb/sq.in
MINM. OIL TEMP. FOR TAKE-OFF .. .. .. 5°C
MAX. CYLR. TKMP. FOR STOPPING ENGINES .. .. .. 230°C

55. Engine Data: Hercules VI, XVI and XVII

(i) Fuel. —100 octane. (The reduced limitations for use with 87 octane fuel are shown in brackets.)

(ii) Oil.—Sec A.P.1464/C37.

(iii) Engine limitations:

  R.p.m. Boost lb/sq.in. Temp. Cyl °C Oil inlet
MAX. TAKE-OFF TO 1,000 FT. M 2,800 +8¼(+5) - -
MAX. CLIMBING M 2,400 +6¼;(+2½) 270 90
I HR LIMIT S 2,500 (2,400) +6¼;(+2½) 270 90
MAX. RICH M
CONTINOUS S
2,400 ++6¼;(+2½) 270(250) 80
MAX. WEAK M
CONTINOUS S
2,400 +2½(zero) 270(250) 80
COMBAT M
5MINS. LIMIT S
2,800* +8½(+5) 280 100
OIL PRESSURE
NORMAL
.. .. .. 80 lb/sq.in
MINIMUM .. .. .. 70 lb/sq.in
MINM. OIL TEMP. FOR TAKE-OFF .. .. .. 5°C
MAX. CYLR. TKMP. FOR STOPPING ENGINES .. .. .. 230°C

* 2,900 on Hercules XVII engines.

+Weak mixture on Hercules XVI and XVII engines is obtained by keeping at or below + 2 lb../sq.in. boost.

56. Flying limitations

(i) These aircraft are designed for manteuvres appropriate to a medium bomber and care must be taken to avoid imposing excessive loads in recovery from dives and in turns at high speeds.

Spinning and acrobatics are not permitted.

(ii) Maximum speeds in m.p.h. (knots) J.A.S.

Diving .. ... ... ... 320(280)

Leigh light lowered...... .. 230 (200)

Undercarriage DOWN .. ... .. 140 (120)

Flaps down to take-off position .. .. 140 (120)

Flaps fully DOWN .. .. .. 120 (105)

Landing lamps lowered .. .. .. 100 (85)

(iii) Maximum weights:

(a) Mark III aircraft:

Take-off and straight flying .. ... 34.500 lb.

All forms of flying and landing ... ...... 29,000 lb.

(b) Mark X, XI, XII, XIII and XIV aircraft:.

Take-off and straight flying .. .. 36,500 lb.

All forms of flying and landing .. .. 30,500 lb.

Note.—On Mark X, Xt and XII aircraft on which Modification No. P. 1603 has not been embodied the maximum A.U.W. is 34.500 lb.

The maximum landing weight for all Marks when used for training purposes is 29,000 lb.

(iv) Bomb clearance angles :

Diving..... 6o°

Climbing ......20°

57. Position error corrections

From 100 130 140 150 170 190 200 220 240 m.p.h.
To 130 140 150 170 190 200 220 240 270 I.A.S.
Add 12 10 8 6 4 2 0 - - m.p.h.
Subtract - - - - - - 0 2 4 m.p.h.
Add 12 10 8 6 4 2 0 - - knots
Subtract - - - - - - 0 2 4 knots

NOTE.—When the A.S.I, is connected to the static vent the above corrections to airspeed can be ignored.

58. Maximum performance

Mark III and X aircraft: (i) Climbing : 130 m.p.h. (115 knots) I.A.S.

Change to S ratio when the boost has fallen by 3 lb./sq.in. (Mk. X aircraft: 2½ lb/sq.in.)

(ii) Combat : Use S ratio if the boost in M ratio is 3 lb./sq.in. below the maximum permitted.

59. Economical flying (see curves Page 32)

(i) Climbing:

Fly at 130 m.p.h. (115 knots) I.A.S. in rich mixture at maximum climbing boost and r.p.m. Change to S ratio when boost has fallen by j lb./sq.in. (Mark III and X aircraft only.) ,

To improve fuel consumption, if temperatures are not excessive, the boost should be followed back with the throttle as far as the economical cruising boost position (Hercules VI or XI). or to the midway position (Hercules XVI or XVII). A weak mixture climb at full load is not recommended, but when used change to S ratio when boost has fallen by 2 lb./sq.in.

(ii) Cruising:

(a) The recommended speeds m.p.h. (knots) I.A.S. are as follows:

Medium and high altitudes:

Fully loaded (outward journey) ..........155 (135)

Lightly loaded (homeward journey) ........140 (125)

Aotc altitudes:

For maximum range ..........160 (140)

For maximum endurance....... 145-150 (125-130)

(A) Fly in weak mixture and M ratio at the maximum permissible boost (on some aircraft this position of the throttle lever is indicated by a white line on the lever coinciding with a pointer on the quadrant, pending the introduction of a warning light) and reduce speed by reducing r.p.m., which may be as low as 1,800 if this will give the recommended speed. If at i.Soor.p.m. the recommended speed is exceeded, reduce boost. (c) Engage S ratio when the recommended speed cannot be maintained at 2,400 r.p.m. (2,500 r.p.m. on Mark III aircraft if using 100 octane fuel), but not below 15,000 feet. (iii) On Mark III aircraft the use of warm air intakes will not appreciably affect air miles per gallon, but on the later Marks they will be reduced by about 5½%.

(iv) The effect of small gill openings when cruising is insignificant.

60. Fuel capacities and consumption

(i) Capacities

(a) Normal:

Two front wing tanks ............................. 300 gallons

Two rear wing tanks .. .. .. 334 gallons

Two nacelle tanks .. .... .. .. 116 gallons

Total .. .. ... ... .. 750 gallons

(b) Long-range (totals):

With one 140-gallon tank ......... 890 gallons

With one 185-gallon tank .. ........ 935 gallons

With one 140-gallon tank and

two 55-gallon tanks ... .... .. 1,000 gallons

With two 140-gallon tanks .. .... ... 1,030 gallons

With one 295-gallon tank .. ... ... 1,045 gallons

With one 185-gallon tank and

one 140-gallon tank .. ... ... 1,075 gallons

With three 185-gallon tanks ..... .. 1,305 gallons

(ii) Hercules XI (Mark III aircraft only) fuel consumptions:

(a) The approximate total consumptions in RICH mixture art as follows:

Boost

lb./sq.in    R.p.m.    Galls./hr.

+6¾    2,800    290

+3½    2,5OO    222

(b) The approximate total consumptions (galls./hr.) in WEAK mixture are as follows:

M ratio at 10,000 ft.
Boost lb/sq.in. 2,400 R.p.m. 2,200 R.p.m 2,000 R.p.m
0 117 - -
-1 111 102 -
-2 104 96 85
-3 96 88 79
-4 87 81 73
S ratio at 15,000 ft.
Boost lb/sq.in. 2,400 R.p.m. 2,200 R.p.m 2,000 R.p.m
0 111 104 -
-1 107 98 92
-2 101 92 87
-3 96 87 81
-4 90 81 75

For every 2,000 ft. above these heights add 1 gall./hr.

For every 2,000 ft. below these heights deduct 1 gall./hr.


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