March, 1937 AIRCRAF T ENGINEERING Instruction s to Ground Engineers and Private Owner s on Essential Modifications No . 1 of the year 1937 airscrew runs smoothly. If rough running is No . 2 of the year 1937 1. Instances have occurred of transverse experienced, the airscrew is to be removed from 1. Trouble has been experienced with the fatigue failure of the blade sheet of Fairey-Reed the hub and the location bolts slacked off and jointing materials used in the fuel tanks of metal airscrews, the fractures commencing at then re-tightened. If, on further tests, rough British Aircraft "Eagle" aeroplanes, Marks th e holes for the hub bolts or the bolts securing running still persists, the airscrew is to be I and II. The tanks affected are those to the returned to th e Fairey Aviation Co. Ltd. , Hayes, th e hub blocks, and extending towards the British Aircraft Manufacturing Company's* Middlesex, for adjustment. leading and trailing edges. Drawing E.18, dated February 16, 1934. In 2. As th e result of these failures, it is necessary 10. The airscrews which are to be subjected some of these tanks the jointing material over that , in future, periodic detail inspection of to detail inspection after periods not exceeding hangs the inner edge of the flanges at the tank these airscrews in the vicinity of the hub blocks 50 hours flying are those numbered as follows, joints and this overhanging portion may sub and identification marks be made. each number being prefixed by the letters sequently break off and obstruct the fuel 3. This detail inspection is to be made, after "F.R.": — system. The British Aircraft Manufacturing each period not exceeding 200 hours flying, of all 371 1247 1469 1496 1566 2079 Company are replacing all these tanks as soon Fairey-Reed metal airscrews. A similar inspec 372 1248 1470 1498 1567 2080 as possible by modified tanks. The modified tion is also to be made, after each intermediate 491 1413 1471 1500 1568 2C81 tanks can be identified by the existence of a period not exceeding 50 hours flying, of the 817 1414 1472 1502 1569 2082 5-in. diameter hand hole in the end remote from airscrews enumerated in para. 10 below, and 927H 1415 1473 1504 1570 2083 th e fuel gauge. of any of those listed in para. 11 which may be 950 1425 1474 1505 1760 2085 2. The fuel tanks of all "Eagle " aeroplanes declared serviceable by the makers. 1135 1427 1475 1506 1761 2101 are to be examined forthwith. If this examina 4. These inspections are additional to the 1189 1429 1476 1507 1762 2103 tion shows that modified tanks (i.e., tanks normal routine inspections, during which the 1191 1460 1477 1508 1862H 2105 with a 5-in. diameter hand hole in the end exposed parts of the blade sheets must be 1193 1461 2274 1481 1509 1863H remote from the fuel gauge) have already been carefully examined for cracks, particularly in 1204 1462 1484 1510 1864H 2278 fitted, no further action need be taken. If the the vicinity of the blade roots and of the deeply 1205 1463 1487 1512 2321 1865H examination shows tha t unmodified tanks (i.e., impressed indentification marks which appear 1233 1464 1488 1513 1925H 2323 tank s without a 5-in. diameter hand hole in the on a few early airscrews of this type. 1243 1465 1491 1515 1929 2324 end remote from the fuel gauge) are fitted, the 5. For the purpose of detail inspection, the 1244 1466 1560 2326 1493 2036 following action should be taken:— airscrews are to be removed from the hubs, 1245 1467 1494 1561 2327 (1) Disconnect the fuel gauges and make a spinners from the airscrews and boss blocks 1246 1468 1495 1564 2039 2686 thorough inspection of the inside of the tanks from the blade sheets. The blade sheets are and any of the airscrews quoted in para. 11 for loose particles of jointing material by then to be cleaned and inspected for cracks, which are declared serviceable after inspection means of a small mirror mounted on a rod. particularly in the vicinity of the bolt holes and b y the makers. (2) Inspect and clean the filters, noting if in regions where any attrition or corrosion has 11. Airscrews of obsolescent design, in view any particles of jointing material are present. occurred. This inspection is to be made with of their age and the possible repairs or adjust (3) Make a flow test. th e aid of a magnifying glass. Inspection for ments made, are to be withdrawn from use 3. If there is detached or loose jointing cracks is facilitated by anodic treatment of the forthwith and returned to the makers for material present in the tanks or filters, the blade sheets, and if this treatment has not inspection, when their serviceability will be owner is advised not to fly the aeroplane until already been given, it is advisable for the blade further considered. These airscrews are num he ha s communicated with the British Aircraft sheets to be anodised as soon as this can be bered as follows, each number being prefixed Manufacturing Company, Ltd., Hanworth Aero arranged. by the letters "F.R.": — drome, Victoria Road, Feltham, Middlesex, 6. Any airscrews found to contain cracks are 1214 238 1485 1759 England. If there is no loose jointing material t o be withdrawn from use, and the matter is 247 1227 1492 1866H present, there is no objection to flying the to be reported to the Secretary, Air Ministry 314 1241 1497 1867H aeroplane pending incorporation of the modified (R.D.A.6), Adastral House, Kingsway, London, 333 1242 1511 1924 tanks, but the inspection referred to in para W.C.2. 489 1250 1514 graph 2 above should be repeated after every 7. If no cracks are found, any attrition or 500 1418 1516 2084 25 flying hours. corrosion marks are to be removed from the 969 1419 1562 2086 4. Ground engineers must not sign Certificates blade sheet and boss blocks by means of coarse 1136 1424 1563 2104 of Safety for Flight for "Eagle " aeroplanes emery followed by fine emery, and the air 1146 1428 1565 2276 unless the above action has been taken. screws are to be re-assembled. During the 1188 1479 1571 2279 5. Certificates of Airworthiness of "Eagle " latte r operation, a layer of tung oil varnish is 1208 1480 1757 2325 aeroplanes will be liable to suspension or to be inserted between the blade sheet and the 1210 1482 1758 2328 cancellation after three months from the date boss blocks and care is to be taken to ensure 12. The Certificate of Airworthiness of an of this Notice unless the tanks have been even tightening of the bolts locating the blocks. aircraft affected by this Notice will be liable to replaced by modified tanks in accordance with When the bolts removed are of the obsolete suspension or cancellation unless the first detail paragraph 1 above or equivalent action taken. type in which the nuts are secured by riveting, inspection has been made, or, where applicable, Januar y 14, 1937. these are to be replaced by new bolts and self- the requirements of para. 11 have been fulfilled, locking nuts obtainable from the Fairey within one month of the date of this Notice : * Formerly the British Klemin Aeroplane Company. Aviation Co. Ltd. exception will be made where airscrews other 8. When spinners are being re-assembled, tha n those quoted in paras. 10 and 11 have not No . 3 of the year 1937 care is to be taken to ensure that there is ye t completed a total of 200 hours flying, the sufficient clearance between the blades and the allowable period being extended until this Cases have occurred of cross levels bursting spinner body to prevent chafing. amoun t of flying has been completed. Certifi when left exposed to the sun in countries with a cates of Airworthiness will not be renewed and hot or moderately hot climate. 9. After re-assembly, and prior to further use, th e airscrews must be checked for blade angles, ground engineers must not sign Daily Certificates The risk of this happening will exist with all track, alignment and static balance, if facilities of Safety for Flight in respect of such aircraft cross levels of the "steel ball " or "bubble " are available. The blade angles at three- after the expiration of the aforementioned typ e in which there is no expansion chamber quarter s of the maximum radius must not periods, unless the requirements of this Notice (the absence of which may be detected by a differ by more than 0° 10'. The difference have been fulfilled. visual examination). It will also be present, between blades, in track and alignment though in lesser degree, where there is an ex 13. If damage occurs to Fairey-Reed metal measured at the tip, must not exceed 1/16 inc h pansion chamber of insufficient capacity. airscrews, repairs must be effected at the and \ inch, respectively. The error in balance I t is therefore recommended that aeroplanes maker's works, except when the repairs are mus t not exceed 5 inch-ounces. Should facilities fitted with either of these types of cross level confined to the removal of scratches and sharp for the above tests not be available, ground should not be left out in the open under a hot nicks in accordance with Notice to Aircraft tests on th e engine, and if these are satisfactory, Owners and Ground Engineers No. 33/1933. sun, unless the cross level is suitably shielded. flight tests, are to be made to ascertain if the Januar y 20, 1937. Januar y 4, 1937.
Aircraft Engineering and Aerospace Technology – Emerald Publishing
Published: Mar 1, 1937
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