AD 75-09-18

woww. apr 26, 1815. nd WILMER D. MIZELL, b) Assistant Secretary For Economic Devélopment. (PR Doc.75-11184 Filed 1-28-75;8:45 am) at Title 14Aeronautics and Space sd CHAPTER I- FEDERAL AVIATION ADMIN- 1- ISTRATION, DEPARTMENT OF TRANS- PORTATION Dr [Docket No. 75-CE-11-AD; Amdt. 39-2190] PART 39AIRWORTHINESS DIRECTIVES AD 72-20-5 (Amendment 39-1526), as Beach Model 18 Airplanes AD 75-09-18 Published as Amendment 39- AD 75-09-18 was revised one time. The revision was published in the Federal Register as amendment 39-2241 to 14 CFR, Part 39 on June 18, 1975, pages 25672 and 25673. amended by Amendment 39-1632 and AD 73-18 4 (Amendment 39-1708) are Air- worthiness Directives (AD) applicable to e Beech Model 18 series airplanes which require repetitive inspections and modi- fications to the center section truss wing spar prior to May 1, 1975, and the outer 2190 to 14 CFR, Part 39 history, subsequent evaluations, analysis As a result of these inspections, service wing panel prior to September 10, 1975. of X-rays and the aircraft structure, the FAA has determined that the airframe Г ing a notice of proposed rule making wing structure is life limited and is issu- (NPRM) that would establish a safe life limit for the basic wing structure of these aircraft. In the interim to assure the continued airworthiness of these aircraft pending development of a final rule un- der the NPRM, this AD is being Issued applicable to all Beech Model 18 series airplanes. The AD includes those aircraft which have accumulated or subsequently accumulate 1,500 hours' time in service since the x-ray submissions required by ADs 72-20-5 and 73-18-4 as well as those aircraft not previously covered. It will require inspections of the elliptical front spar lower cap of the wing center section, outer wing panel and the upper spar cap at station 90 for the detection of cracks and the submission of X-rays to the manufacturer for evaluation. ฿9, 1975 Federal Register, Volume 40 - April 29, 1975 Page 18544

RULES AND REGULATIONS 18545 expeditious adoption of the amendment, Bince a situation existe which requires equipment as necessary to eliminate inter- (3) Temporarily move clamps and other of the spar cap material near the inspeo- tion site is 1.5 to 3.8 on the densitometer or me by the Administrator, 14 CPR 11.89 pursuant to the authority delegated to than thirty (30) days. impracticable and good cause exists for making the amendment effective th less notice and public procedure hereon are In consideration of the foregoing and ference with the above inspections. Removal graph C by applying and rellering • 78 to 100 on the (left or right) side being inspected. pound upward force at or near the wing tip of spar cap Anish is not necessary. This may be done by hand. (4) Loed the wing on the alde being in- (3) Flex the wing when specided by Para- cap 0.010 inch diameter hole in the penetrameter, and ite entire outline are plainly abown. Us- graph for faint indications of cracks in spar ing a low power magnifying device, examine the inspection National Bureau of Standards density scale. View him to see that the inspection site, the material transverse to the spanwisd site portion of each radio- (31 PR 13897), $ 39.13 of Part 39 of the spected when specifled by Paragraph C by centorime. Federal Aviation Regulations is amended by adding the following new AD. the junction of wing rib number 10 and the applying 75 to 100 pound upward force at front sper, Place material auch as humber D. On those aircraft modifed by incor- Bazen. Applies to all Beech 18 series airplanes under and along the number 10 rib so as to lower cap of the wing center section, outer 20-5 and 73-18-4 were applicable, within to detect cracks in the elliptical front spar wing panel and upper spar cap at station 90: (a) For those aircraft to which ADs 72- To prevent possible wing failure, in order plemental Type Certificates. including planes modified in accordance with Bup- whereor and those Beech Model 18 military counterparts air- being flexed. Use a fashlight or other illum!- and after cleaning, and while the wing is nation and a low power magnifying device. choson, conduct the inspection while the inspection before magnetiam is induced and again while magnetism across the inspection wing is either flexed or loaded. Conduct the distribute the force (2) When the magnetle particle method is C. (1) Accomplish visual inspection before the inspections required by Paragraphs B manufacturer or STC holders as applicable and C, remove the strep assemblies in ac- or any other such modinention approved by the Chief, Engineering and Manufacturing cordance with procedures specifed by the and Inspect all components of the strap as- sembly for defects such as cracks, corrosion, fretting, etc. If defects are found in these Branch/Division, FAA, prior to performing on each 18-4024, 791 or 793: following: Paragrapa B. inforced by Beech Aircraft Corporation Kits affective date of this AD, accompliab the (1) or Figure (3) of an PAA-spproved equiva- the wing center section and outer wing panel specified below, including inspection sites re- lent to facilitate the inspections specined in 50 hours' time in service after the effectivo date of this AD, whichever occurs later, and lower wing skin in accordance with Figure X-ray submisalon for evaluation or within 1,560 hours' time in service aince the last save not been submitted vithin 50 hours' time in service after the B. (1) Inspect the front spar lower cap of (b) On all other aircraft for which I-rays A. Unless previously modided, modify the side of the airplane by methods for evaluation, on the upper surface of the spar cap (over 81, etc.), date, and airplane registration num- an inspection site) with identification sym- alte la critical to the oraluation of the I- ber. Proper identification of the inspection Instructions. Inspection while the wing is loaded. Figures 4, 5 and 8 are alds to the following instruc- tion. Place fine grain film (auch as GAF 800, Dupont NDT-65 or Kodak AA) sandwiched between lead screens of 0.005 inch thickness bols for at least the alte (e.g. LWS 81, RWE perform the inspection while the wing is specined by Paragraph B, accomplish X-ray site is induced by a Magnadux Corp. Model Y& or YM-6 Joke or when any equivalent is being flexed. Use either dye or guorescent materials in accordance with the penetrant used in accordance with the manufacturer's manufacturer's instructions. (3) When the penetrant method is chosen, (4) For each site where X-ray inspection i Branch, PAA, Contral Region, stating the 1o- Chief, cation and length of any cracks discovered Chief, Beech Atreraft Corporation. components as a result of any such inspec- fective components with new airworthy parts tions within 48 hours Beech Aircraft Corporation, Wichita, Kansas to service untll authorized in writing by the Branch, FAA, Central Region. In addition, written notification must be sent to the rapid means, coples of all the spections required by Paragraphs B and O of this AD, the aircraft shall not be returned 67201. Evaluation of the inspection facility tions, prior to further fight, replace the de- indings will be tranamitted to the sender by F. If a crack is found as a result of i- E. Upon completion of the above inspec- Engineering Engineering and Manufacturing and Manufacturing transmait, -rays to by most Wing station Bite (see fig. 3) Metbod rays. The left side of the aircraft (left wing) during inspections required by this AD, and ace para. C) is the side to the left of the pilot when fac- the total operating time of the airplane at ing forward. For upper wing station 90, the the time of the diecovery. (Reporting ap- sa (apper Tipe of welds at Visual, X-ray plate is to be placed on the lower surface of proved by the Ouice of the Management and 1, 72,61 крат сер). ana ower Tipe of welde at clevis tangs, upper of cap. and lower surfaces and either magnetic particle or penetrant. Do. inch thicknem to the lower surface of the cated wing. Secure a steel penetrameter of 0.005 the upper apar cap with the s-tay source lo- approximately 36 inches above the poration's Service Bulletins 64-15, 64-18, Bndget under OMB No. 04-R0174.) Currently effective Beech Aircraft Cor- and 57 surface of cap. gussets, upper spar cap at a location clear of the inspection 64-17; and 86-10 and MIL-STD-453 con- 29... Outboard ends of and lower surface splice in cap, upper Do. alte. Poaition the X-ray source approximately 86 Inches from and generally below the fim so that the center of the I-ray beam wil! be sider this subject, but this AD takes precedence in any conflicting detail. #_.. 85 to 12. Tip of weld around esp. cluster upper Do. Do. wise conterline of the spar cap at each inspec- perpendicular to the major axis of the ellip- tical spar cap and perpendicular to the span- tion site. Use & flashlight and a protractor May 1, 1875. (Secs. 313(a), 001 and 603 Federal Aviation Act of 1958 This amendment becomes effective (49 U.9.C. 1354(2), 1421 and Lover surface of spar murface of cap. Doi level as necessary to see that alming of the tion Act (49 U.S.C. 1655 (c))) 1429), sc. 6(c) Department of Transporta- cap belor tube X-ray beam compensates for wing dihedral from wheel well. cluster, as meer she hose up attitude. At those areas covered Issued in Kansas City, Missourl, on 102 and 111.. Lips of the weld sa Do. by aluminum skin, & locally fabricated Jig April 17, 1875. shown in fige. 5 and e may be used to position the X-ray source. C. R. MELUGIN, JI., Expose film ao that denalty of the radlograph Director, Central Repion, Federal Register, Volume 40 - April 29, 1975 Page 18545

RULES AND REGULATH or Wingratkin -Locato Nam In Joggle aver Eniaring Damblar in this Area ocrewa 19 places. •KING DOWN ON LOWER WINGSHIN / SPAR Wineskin O mitred for Clarity) FIGURE Federal Register, Volume 40 - April 29, 1975 Page 18546 - Ken Mib (Upper Midzzing Dumbler. Entering Caesa 280aut (29) 00499 arach doublers 18546

VIEW LOOKING DOWN ON LOWER WINGSKIN AND SPAR TUBE Nurplare Earlong Skin 202459 wirh .ars • VIEW A-A INSPECTION PLATE AFT SOLING Enisting Doubler per Elech Sa Laur, Wingstin - Firer Stringer Kad a Sadepend *BuinTack He 90tg-T3 Angle Exiaring Lur, Skin Nutplato VIEW A-A Federal Register, Volume 40 - April 29, 1975 Page 18546 Rib i Nose by Dait Graber Ye Blind Existin Places Fastering My (t) •d(7) 2024-55 Alum. Allew ½ " and all acrest (mia). tamar elde with $10 as) ; cur three holes cass- Inspection door FIGURE 2

Sear Tuba. RULES AND Half of Main Sper Center Section Truss INDES, 10DE INTER THIS A.D. FIGURE 3 Federal Register, Volume 40 - April 29, 1975 Page 18547 Wing Firtings

Тиб. for Crack Ind (inspection site) EXAMPLE CARED SCORPH JOINT Verrical Tuba- eWeld Inspection Sires JACKPAD & SPLICE GUSTET D Spar Tibe Federal Register, Volume 40 - April 29, 1975 Page 18547 SIDE VIEW SHOWING SETUF FOR NOSE-UP ATTITUDE FIGURE 4 Allanment Source FRONT VIEW #OR SHOWING GETUF DIHEDRAL - TYPICAL GÜSSETED JOINT

FIGURE 5 Rib Numbera Dou ACE - SPAR ç0 Spr Rib Numbers Wing Station, Ws I11 102 Egu Inspection Areas WingHinge (Ref) JACK SCALE STAND Apply 75 10 100 165 as Shourn Film - FIBI ONLY ot Tip of Wing Boing X-Fayed (Ser Fig?) Penetramater Position X-Ray Source for Two Shots Parallel to Plane of Rib, Source Approx, 36 Fram Film Position X-Ray Plans of Spar to Plana of Mih- Source Parallal source Approx- 3G" From Film. ALTERNATE METHOD for X-RAYING WS 102 ONLY calm RIB 1 or 2 2 shots - This Method only One. Method shown at left reguires (800 Fig 2)- Penetramerer Normal to 7-Ray Baam on Position Sage Side as Sourco 102 Angle, € 45° 20° And For NOSE-UP ATTITUDE AFTER WING LOAD ISAFPLIED, COMPENSATE For DIHEDRAL- Federal Register, Volume 40 - April 29, 1975 Page 18548 FEDERAL REGISTER, VOL, 40. NO. 83T11

FIGURE 6 EXAMPLE of X'RAY FILM at Requirad WS III Panctrometar Double Film to Hole Dia- Accomodate 0.166" •005 f 0.356 Thicknees .010 Spar Cap Material. коРАК AA $ M or .007 .014 • 020 Equivalent. N123Z 8-19-73 RWS I!! Required Idantification LEGEND Of INSPECTION SITES SYMBOL Tips of Tang Welds, Top f Bottom of Spar Tube DESCRIPTION NO. of BITES/WING RULES AND REGULATIONS Edges of Thru-Bolt Tube Weld? 1Ç Edges of Diagonal Brace Welde Tipe of' Fishmourh' Splice Welds, Top f Bottom of Spar Tube EXAMPLE of X-RAY FILM at WS 102 Single Film for 0.19 "Thickness Spar Cap Material. KODAK AA or M or Equivalent- N123Z 8-19-73 AWS 10Z required Identification [FR Doc.75-10871 Filed 4-26-75;8:48 am] Federal Register, Volume 40 - April 29, 1975 Page 18548