SERVICE KIT thru , 631, 634, 675 R thru R F thru F FR thru FR
|
|
- Oswin Lane
- 6 years ago
- Views:
Transcription
1 TITLE SEAT BELT AND SHOULDER HARNESS KIT INSTALLATION EFFECTIVITY MODEL SERIES SERIAL NUMBERS thru , 631, 634, 675 R182 R thru R F182 F thru F FR182 FR thru FR DESCRIPTION To replace existing seat belts with new seat belts and shoulder harnesses with metal-to-metal buckles. APPROVAL FAA approval has been obtained on technical data in this publication that affects airplane type design. For Reims Aviation airplanes: DGAC approval has been obtained on technical data in this publication that affects airplane type design. REFERENCE SEB92-28 Single Engine September 4, 1992 Revision B - May 5, 2000 Page 1 of of 23 To obtain satisfactory results, procedures specified in this publication must be accomplished in accordance with accepted methods and prevailing government regulations. The Cessna Aircraft Company cannot be responsible for the quality of work performed in accomplishing the requirements of this publication. The Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, Kansas 67277, U.S.A. (316) Facsimile (316) COPYRIGHT 1992
2 CHANGE IN WEIGHT AND BALANCE Each seat belt and shoulder harness assembly (including airframe attachment parts) will increase the airplane s empty weight by 0.75 pound at each seat location and should be included as part of the airplane s basic empty weight. For 1975 and earlier model airplanes, refer to the airplane s weight and balance data and equipment list to determine the location (arm) of each seat. For 1976 and later model airplanes, refer to Section 6, Weight & Balance/Equipment List, of the Pilot s Operation Handbook to determine the location (arm) of each seat location. MATERIAL INFORMATION Airplanes Model 182, thru , 613, and, 631, order one (1) 1 kit for the cockpit shoulder harness installation. Page 2 PART NUMBER QUANTITY DESCRIPTION 1 1 Kit, consisting of the following parts: AN R9 14 Screw MS20426AD3-5A 8 Rivet MS20470AD3-5A 4 Rivet MS21042L4 4 Nut MS21044N08 14 Nut MS21047L4 2 Nutplate NAS1149F0663P 4 Washer NAS1149FN832P 14 Washer NAS43HT Spacer NAS464P4A12 2 Bolt S1021Z6-6 2 Screw Cover Gusset, Right Gusset, Left Spacer Harness Assembly 1 Instructions
3 Airplanes Model 182, thru and 634 order one (1) 2 kit for the cockpit shoulder harness installation. Airplanes Model 182, thru , and 675; Model R182, R thru R ; Model F182, F thru F ; and Model FR182, FR thru FR , order one (1) 2 kit for the passenger shoulder harness installation. Airplanes Model 182, thru , 613 and 631, order one (1) 3 kit for the passenger shoulder harness installation. Page 3 PART NUMBER QUANTITY DESCRIPTION 3 1 Kit, consisting of the following parts: AN43B4A 2 Eye Bolt MS20426AD3-4A 8 Rivet MS20470AD4-4A5 8 Rivet MS21042L4 4 Nut MS21042L3 2 Nut MS21044N4 2 Nut MS21047L3 2 Nutplate MS Screw NAS1149F0332P 2 Washer S Harness Assembly Strap Hook Spring 1 Instructions PART NUMBER QUANTITY DESCRIPTION 2 1 Kit, consisting of the following parts: AN3-4A 2 Bolt MS20470AD3-4A 8 Rivet MS20470AD3-6A5 4 Rivet MS20470AD4-5A 8 Rivet MS21042L4 4 Nut MS21059L4 2 Nutplate NAS1149F0432P 2 Washer NAS1149F0463P 2 Washer NAS1149F0663P 4 Washer NAS43HT Spacer NAS43HT Spacer NAS464P4A10 2 Bolt NAS464P4A13 2 Bolt NAS464P4A14 2 Bolt NAS464P4A8 2 Bolt S Spacer Cover Doubler, Right Doubler, Left Spacer Harness Assembly 1 Instructions
4 Airplanes Model 182, thru , and 634, order one (1) 4 kit for the passenger shoulder harness installation. ACCOMPLISHMENT INSTRUCTIONS 1. Install the cockpit shoulder harness assembly. Installation is typical for left and right side. A. Remove and discard existing seat belts. Retain attaching hardware for reinstallation, except nut, which may be discarded. B. Loosen headliner and remove headliner retainer and right window molding to gain working access, as required. C. Disconnect utility light and remove left window molding. D. Airplanes thru , 613 and 631: (1) Remove existing gusset. (2) (Refer to Figure 1, Sheet 1, Detail A.) Airplanes with Detail A. configuration, install the (left) or (right) gusset. Page 4 PART NUMBER QUANTITY DESCRIPTION 4 1 Kit, consisting of the following parts: MS21042L4 4 Nut NAS1149F0463P 2 Washer NAS1149F0663P 4 Washer NAS43HT Spacer NAS464P4A12 2 Bolt S Spacer S Rivet Harness Assembly Cover Plate Assembly - Left Plate Assembly - Right 1 Instructions
5 (a) Using the existing gusset as a template, match drill seven (7) 11/64 (0.172) inch diameter holes in the new (left) or (right) gusset and existing lower headliner retainer. (b) Position the new (left) or (right) gusset on the doorpost and match drill four (4) 11/64 (0.172) inch diameter holes from gusset in doorpost. Secure using temporary sheet metal fasteners in top three (3) holes. (c) Position the new gusset on the doorpost and match drill three (3) 11/64 (0.172) inch diameter holes from gusset in door sill assembly. (d) Using the existing lower aft hole in the headliner retainer as a template, mark and drill one (1) 11/64 (0.172) inch diameter hole thru headliner retainer and doorpost. Secure using a temporary sheet metal fastener. Hole may require pulling slightly to ensure a minimum of 0.25 inch edge distance is maintained while drilling. (e) Match drill one (1) Number 40 (0.098 inch diameter) hole in the headliner retainer thru the gusset. Secure using a temporary sheet metal fastener. (f) Using the existing gusset as a template, mark hole location for nutplate on headliner retainer. (g) Drill one (1) Letter F (0.257 inch diameter) hole in headliner retainer and new gusset. Remove parts. (h) Position the MS21047L4 Nutplate on the gusset and match drill two (2) Number 40 (0.098 inch diameter) holes in gusset. Countersink 100 x 0.18 diameter to match MS20426AD3-5A rivet. (i) Install the MS21047L4 Nutplate on the gusset using two (2) MS20426AD3-5A Rivets. (j) Position the gusset on the doorpost and install three (3) AN R9 Screws, NAS1149FN832P Washers and MS21044N08 Nuts thru the gusset and doorpost. (k) Install three (3) AN R9 Screws, NAS1149FN832P Washers and MS21044N08 Nuts thru the gusset and door sill assembly. (l) Position the headliner retainer on the gusset and install one (1) AN R9 Screw, NAS1149FN832P Washer and MS21044N08 Nut in headliner retainer, gusset and doorpost. Trim and hand form headliner retainer, as required, to match the contour of gusset. Notch headliner retainer at bend to prevent buckle. (m) Install one (1) S1021Z6-6 Screw thru the headliner retainer and doorpost. It is permissible to relocate hole to maintain 0.25 inch minimum edge distance. (n) Install one (1) MS20470AD3-5A Rivet in headliner retainer, gusset and sill assembly. (o) Reinstall headliner and window molding in original position. (p) (Refer to Figure 1, Sheet 9, Detail L.)Install the Harness Assembly using two (2) NAS1149F0663P Washers and one (1) Spacer, NAS43HT4-22 Spacer, NAS464P4A12 Bolt and Cover (3) (Refer to Figure 1, Sheet 2, Detail B.) Airplanes with Detail B. configuration, install the (left) or (right) gusset. (a) Using a putty knife, or equivalent, separate the upper and lower headliner retainer at spot weld locations. Page 5
6 (b) Position the gusset on the lower headliner retainer and, using the existing gusset as a template, match drill seven (7) 11/64 (0.172) inch diameter holes. (c) Measure and mark a line 1/2 (0.50) inch below center line of second hole in aft edge of gusset, extending to forward edge of gusset. (d) Measure and mark a line 1/2 (0.50) inch aft of forward, diagonal edge of gusset. (e) Drill one (1) Letter F (0.257 inch diameter) hole at cross section where lines intersect. (f) Position nutplate over hole and mark and drill two (2) Number 40 (0.098 inch diameter) holes thru gusset. Countersink 100 x 0.18 diameter to match MS20426AD3-5A rivet. (g) Install MS21047L4 Nutplate on gusset using two (2) MS20426AD3-5A Rivets. (h) Position the new gusset and lower headliner retainer on the doorpost and match drill three (3) to 11/64 (0.172) inch diameter holes in the doorpost. Secure using temporary sheet metal fasteners. Trim and hand form lower headliner retainer, as required, to match contour of gusset. (i) Match drill three (3) 11/64 (0.172) inch diameter holes in the gusset thru lower headliner retainer and door sill assembly. Secure forward hole using a temporary sheet metal fastener. (j) Align the aft corner of the upper headliner retainer with the aft corner of the gusset and the contour of sill assembly. Trim and hand form lower headliner retainer, as required, to match contour of gusset. (k) Using the forward existing hole in the upper headliner retainer as a template, drill one (1) Number 40 (0.098 inch diameter) hole thru the gusset and lower retainer. Secure using a temporary sheet metal fastener. (l) Drill one (1) 11/64 (0.172) inch diameter hole thru the upper headliner retainer, gusset, lower headliner retainer and the doorpost. Remove upper headliner retainer. (m) Secure gusset and lower headliner retainer using three (3) AN R9 Screws, NAS1149FN832P Washers and MS21044N08 Nuts in top three (3) holes in gusset, lower headliner retainer and doorpost. (n) Secure gusset and lower headliner retainer using three (3) AN R9 Screws, NAS1149FN832P Washers and MS21044N08 Nuts, lower headliner retainer and sill assembly. (o) Position the upper headliner retainer on the gusset and secure using one (1) AN R9 Screw, NAS1149FN832P Washer and MS21044N08 Nut in upper headliner retainer, gusset, lower headliner retainer and doorpost. (p) Install one (1) MS20470AD3-5A Rivet in upper headliner retainer, gusset and lower headliner retainer. (q) Reinstall existing screws in lower headliner retainer along sill assembly. (r) Reinstall headliner and right window molding in original position. (s) Reconnect utility light and install left window molding. (t) Press on headliner to locate nutplate and, using a sharp instrument, pierce headliner at nutplate location. (u) (Refer to Figure 1, Sheet 9, Detail L.) Install Harness Assembly using two (2) NAS1149F0663P Washers and one (1) Spacer, NAS43HT4-22 Spacer, NAS464P4A12 Bolt and Cover. Page 6
7 E. Airplanes thru and 634: (1) (Refer to Figure 1, Sheet 3, Detail D. and Sheet 4, View A-A.) Loosen window molding and headliner, as required, to gain access to the doorpost assembly at (2) Remove three (3) existing rivets in gusset. (3) Drill upper pilot hole in (left) or (right) Doubler to Number 30 (0.128 inch diameter). (4) Position doubler on doorpost and secure using temporary sheet metal fasteners. (5) Match drill hole in lower gusset, thru the doubler, to Number 30 (0.128 inch diameter). Remove doubler. (6) Lay out and drill lower hole location in doubler on doorpost to Number 40 (0.098 inch diameter). (7) Lay out nutplate screw hole location on doorpost using existing fastener location. (8) Reposition doubler on doorpost and secure using temporary sheet metal fasteners. (9) Enlarge nutplate screw hole location to Letter F (0.257 inch diameter). CAUTION: ENSURE A MINIMUM OF 0.42 INCH EDGE DISTANCE IS MAINTAINED WHILE ENLARGING SCREW HOLE. (10) Remove doubler, then mark and drill final nutplate rivet location to Number 40 (0.098 inch diameter). Countersink 100 x 0.18 diameter to match MS20426AD3-5A rivet. If it is desired to be able to replace the MS21059L4 Nutplate without removing the Doubler, install the doubler and nutplate per the following procedures: a Do not countersink doubler to match MS20426AD3-5A rivet. b Reposition doubler on doorpost and secure using temporary sheet metal fasteners. c Back-drill the two nutplate rivet locations thru doorpost. d Install MS21059L4 Nutplate on doubler and doorpost using two (2) MS20470AD3-6A5 Rivets. Proceed to step 1.E.(12). (11) Install MS21059L4 Nutplate on doubler using two (2) MS20426AD3-4A Rivets. (12) Install doubler on doorpost using two (2) MS20470AD4-5A Rivets. (13) Pierce headliner at nutplate location. (14) Using a hole finder, locate nutplate and drill one (1) Letter F (0.257 inch diameter) hole thru headliner retainer to match nutplate. (15) Reinstall headliner, headliner retainer and right window molding in original position. (16) Reconnect utility light and reinstall left window molding. (17) (Refer to Figure 1, Sheet 9, Detail M.) Install Harness Assembly using one (1) Spacer, two (2) NAS1149F0663P Washers, and one (1) NAS43HT4-22 Spacer, Cover, one (1) NAS1149F0463P Washer and NAS464P4A13 or NAS464P4A14 Bolt. Ensure the installed bolt shank is not contacting the nutplate threads and that there is sufficient bolt/nutplate thread engagement. Page 7
8 2. Install passenger shoulder harness. Installation is typical for left and right side. A. Remove existing seat belts. Retain attaching hardware for reinstallation, except nut, which may be discarded. B. Airplanes thru , 613 and 631: (1) (Refer to Figure 1, Sheet 5, Detail E.) Loosen headliner and window molding to gain working access, as required. (2) (Refer to Figure 1, Sheet 5, Detail F.) Remove existing rivet in skin and bulkhead at approximately BL (3) (Refer to Figure 1, Sheet 6, Detail G.) Lay out and drill two (2) Number 40 (0.098 inch diameter) holes in Strap. (4) Position strap on bulkhead at and back drill two (2) Number 30 (0.128 inch diameter) holes. (5) Install strap on bulkhead at using two (2) MS20470AD4-4A5 Rivets. (6) Using the MS21047L3 Nutplate as a template, layout and drill two (2) Number 40 (0.098 inch diameter) holes thru strap and bulkhead at (7) Again, using the nutplate as a template, drill one (1) Number 10 (0.193 inch diameter) hole to match nutplate. (8) Install nutplate on strap and bulkhead at using two (2) MS20426AD3-4A Rivets. (9) Reinstall headliner and window molding in original position. (10) Press on headliner to locate nutplate and, using a sharp instrument, pierce headliner in nutplate location. (11) (Refer to Figure 1, Sheet 6, Detail H.) Install S Harness Assembly using one (1) Hook, Spring and MS Screw. C. Airplanes thru : (1) (Refer to Figure 1, Sheet 7, Detail I.) Loosen rear upholstery panel, as required, to gain working access to bracket. (2) Locate existing bracket at station , along lower edge of back window. Remove and discard existing nut and bolt. (3) Enlarge vacated hole by drilling one (1) inch diameter hole. (4) Install one (1) AN43B4A Bolt in enlarged hole and secure using one (1) MS21044N4 Nut. (5) Trim rear upholstery panel, as required to clear bolt, and reinstall in original position. (6) Install S Harness Assembly using one (1) Hook, Spring, MS Screw, and MS21042L3 Nut, and two (2) NAS1149F0332P Washers. Page 8
9 D. Airplanes thru , and 634. Installation is typical for left and right side. (1) (Refer to Figure 1, Sheet 8, Detail J.) Remove window molding and upholstery panels as required to gain working access to Stiffener. (2) Position Plate assembly over Stiffener as shown in Detail J. (3) Using the pilot holes in the Plate assembly as a template, match drill 18 Number 30 (0.128 inch diameter) holes thru Plate assembly and Stiffener. Ensure there is an appropriate edge distance between the number 30 holes and the radius of the Stiffener. (4) Deburr holes, install Plate assembly on Stiffener using 18 S rivets. (5) Reinstall rear upholstery panel and window molding. (6) Locate nutplate at and drill one (1) Letter F (0.257 inch diameter) hole thru window molding to match nutplate. (7) Install Harness Assembly as follows: (a) (Refer to Figure 1, Sheet 10, Detail P.) Install harness assembly using one (1) S Spacer two (2) NAS1149F0663P Washers and one (1) NAS43HT4-22 Spacer, and one (1) Cover, one (1) NAS1149F0463P Washer and one (1) NAS464P4A12 Bolt. E. Airplanes thru , 675, R thru R , F thru F , and FR thru FR (1) (Refer to Figure 1, Sheet 9, Detail K and L.) Loosen window molding to gain working access. (2) Locate existing nutplate at and drill one (1) Letter F (0.257 inch diameter) hole thru window molding to match nutplate. (3) Secure window molding in original position. (4) Install Harness Assembly as follows: (a) (Refer to Figure 1, Sheet 10, Detail P.) Airplanes thru , install harness assembly using one (1) S Spacer two (2) NAS1149F0663P Washers and one (1) NAS43HT4-22 Spacer, and one (1) Cover, one (1) NAS1149F0463P Washer and one (1) NAS464P4A12 Bolt. (b) (Refer to Figure 1, Sheet 10, Detail Q.) Airplanes thru and 675; R thru R ; F thru F ; and FR thru FR , install harness assembly using two (2) NAS1149F0663P Washers and one (1) NAS43HT4-22 Spacer, Cover and NAS464P4A8 or NAS464P4A10 Bolt. Ensure the installed bolt shank is not contacting the nutplate threads and that there is sufficient bolt/nutplate thread engagement. Page 9
10 3. Install seat belts. A. (Refer to Figure 2, Sheet 1, Detail A.) Install cockpit seat belts as follows: (1) Install seat belt half with the the link assembly on the outboard side of cockpit seat, as shown, and secure using existing hardware and one (1) MS21042L4 Nut. (2) Install seat belt half with buckle on the inboard side of the cockpit seat, as shown, and secure using existing hardware and one (1) MS21042L4 Nut. B. Install passenger seat belts. If seat belt installation requires the removal of seat, discard existing nuts and replace with new nuts. (1) Airplanes thru : (a) (Refer to Figure 2, Sheet 3, Detail E.) Install seat belt half with the the link assembly on the inboard side of passenger seat, as shown, and secure using existing hardware and one (1) MS21042L4 Nut. (b) (Refer to Figure 2, Sheet 1, Detail B.) Install seat belt half with buckle on the outboard side of the passenger seat, as shown, and secure using existing hardware and one (1) MS21042L4 Nut. (2) Airplanes thru , 613, 631; thru , 634, 675; and F thru F : (a) (Refer to Figure 2, Sheet 2, and 3, Detail C., E., and F.) Install seat belt half with the buckle on the inboard side of passenger seat, as shown, and secure using existing hardware and one (1) MS21042L4 Nut. (b) (Refer to Figure 2, Sheet 1, Detail B) Install seat belt half with link assembly on the outboard side of the passenger seat, as shown, and secure using existing hardware and one (1) MS21042L4 Nut. (3) Airplanes; R thru R ; and FR thru FR : (a) (Refer to Figure 2, Sheet 2, Detail D.) Install seat belt half with buckle on the inboard side of the passenger seat, as shown, and secure using existing hardware and secure using two (2) NAS1149F0432P Washers, and one (1) AN3-4A Bolt, NAS43HT4-11 Spacer and MS21042L4 Nut. (b) (Refer to Figure 2, Sheet 1, Detail B.) Install seat belt half with link assembly on the outboard side of the passenger seat, as shown, and secure using existing hardware and one (1) MS21042L4 Nut. 4. Adjust harness assembly as follows: A. To snug up shoulder strap, pull down on lower free end of strap. B. To loosen shoulder strap, pull up on cloth tab attached to lower adjustment fitting. 5. Make an entry in the airplane logbook stating this service kit has been installed. Page 10
11 Page 11 Figure 1. Shoulder Harness Installation (Sheet 1 of 9) ABC K E NUTPLATE LOCATION MAY VARY SLIGHTLY TO ENSURE NO INTERFERENCE WITH STRUCTURE IS PRESENT. DETAIL A LOOKING OUTBOARD AT COCKPIT GUSSET INSTALLATION (LEFT SIDE SHOWN, RIGHT SIDE OPPOSITE) THRU , 613 AND 631 TRIM AND HAND FORM HEADLINER RETAINER TO MATCH GUSSET AND DOOR SILL NUMBER 40 (0.098 INCH DIAMETER) HOLE MS20426AD3-5A RIVET (2 REQUIRED) (LEFT) (RIGHT) GUSSET NOTCH RETAINER AT BEND PRIOR TO HAND FORMING TO PREVENT BUCKLE 11/64 (0.172 INCH DIAMETER) HOLE TO MATCH EXISTING GUSSET AN R9 SCREW NAS1149FN832P WASHER MS21044N08 NUT (7 REQUIRED) REAR DOORPOST LETTER F (0.257 INCH DIAMETER) HOLE MS21047L4 NUTPLATE TO MATCH GUSSET AND HEADLINER RETAINER UP FWD BRACKET MS20470AD3-5A RIVET 11/64 (0.172 INCH DIAMETER) HOLE RELOCATE TO MAINTAIN 0.25 MINIMUM EDGE DISTANCE IF NECESSARY S1021Z6-6 SCREW (1 IF REQUIRED) THRU , 613 AND 631 USE COCKPIT GUSSET INSTALLATION, DETAIL A OR DETAIL B, AS APPLICABLE TO AIRPLANE CONFIGURATION DOOR SILL
12 Page 12 Figure 1. Shoulder Harness Installation (Sheet 2) DETAIL B COCKPIT HARNESS INSTALLATION THRU AND 631 (LEFT SIDE SHOWN, RIGHT SIDE OPPOSITE) UP FWD REAR DOORPOST ALIGN LOWER AFT CORNER OF HEADLINER RETAINER WITH GUSSET HEADLINER RETAINER USE A PUTTY KNIFE, OR EQUIVALENT, TO SEPARATE HEADLINER RETAINERS AT SPOT WELD LOCATIONS (LEFT) (RIGHT) GUSSET MS20470AD3-5A RIVET LETTER F (0.257 INCH DIAMETER) HOLE MS21047L4 NUTPLATE NUMBER 40 (0.098 INCH DIAMETER) HOLE MS20426AD3-5A RIVET (2 REQUIRED) 11/64 (0.172) INCH DIAMETER HOLE TO MATCH EXISTING GUSSET AN R9 SCREW NAS1149FN832P WASHER MS21044N08 NUT (7 REQUIRED) 0.50 NUTPLATE LOCATION MAY VARY SLIGHTLY TO ENSURE NO INTERFERENCE WITH STRUCTURE IS PRESENT THRU , 613 AND 631 USE COCKPIT GUSSET INSTALLATION, DETAIL A OR DETAIL B, AS APPLICABLE TO AIRPLANE CONFIGURATION. USE A PUTTY KNIFE, OR EQUIVALENT, TO SEPARATE HEADLINER RETAINERS AT SPOT WELD LOCATIONS
13 Page 13 Figure 1. Shoulder Harness Installation (Sheet 3) DETAIL C LOOKING FORWARD AT DOORPOST (LEFT SIDE SHOWN, RIGHT SIDE OPPOSITE) D (RIGHT) (LEFT) DOUBLER (RIGHT) (LEFT) DOUBLER DETAIL D LOOKING FORWARD AT DOUBLER INSTALLATION THRU , AND 634 (LEFT SIDE SHOWN, RIGHT SIDE OPPOSITE) INBD UP NUMBER 40 (0.098 INCH DIAMETER) HOLE COUNTERSINK 100 X 0.18 DIAMETER MS20426AD3-4A RIVET (2 REQUIRED) PICK UP EXISTING FASTENER NUMBER 30 (0.128 INCH DIAMETER) HOLE MS20470AD4-5A RIVET (2 REQUIRED) WL (TYPICAL) A A
14 Page 14 Figure 1. Shoulder Harness Installation (Sheet 4) VIEW A-A LOOKING OUTBOARD AT DOUBLER INSTALLATION (LEFT SIDE SHOWN, RIGHT SIDE OPPOSITE) FWD UP NUTPLATE SPAR CARRY THRU OUTER BULKHEAD CHANNEL INNER BULKHEAD CHANNEL , RIGHT , LEFT DOUBLER MS20426AD3-4A RIVET 0.42 PICK UP EXISTING FASTENER LETTER F (0.257 INCH DIAMETER) HOLE THRU DOORPOST AND DOUBLER MS21059L4 NUTPLATE
15 Page 15 Figure 1. Shoulder Harness Installation (Sheet 5) DETAIL F LOOKING OUTBOARD AT PASSENGER HARNESS INSTALLATION SEATS THREE AND FOUR THRU , 613 AND 631 (RIGHT SIDE SHOWN, LEFT SIDE OPPOSITE) F FWD UP DETAIL E PASSENGER HARNESS INSTALLATION (RIGHT SIDE SHOWN, LEFT SIDE OPPOSITE) I J SKIN BULKHEAD MS SCREW SPRING HOOK S HARNESS UP FWD B G B SKIN BULKHEAD STRAP REMOVE EXISTING FASTENER VIEW B-B LOOKING AFT AT PASSENGER HARNESS INSTALLATION (RIGHT SIDE SHOWN, LEFT SIDE OPPOSITE) STRAP MS SCREW FRAME BL MS21047L3 NUTPLATE
16 Page 16 Figure 1. Shoulder Harness Installation (Sheet 6) DETAIL H LOOKING AFT AT PASSENGER HARNESS INSTALLATION (RIGHT SIDE SHOWN, LEFT SIDE OPPOSITE) DETAIL G LOOKING DOWN AT STRAP INSTALLATION (RIGHT SIDE SHOWN, LEFT SIDE OPPOSITE) MS21047L3 NUTPLATE SPRING HOOK BULKHEAD S HARNESS MS SCREW STRAP E PICK UP EXISTING RIVET HOLE IN BULKHEAD FLANGE NUMBER 40 (0.098 INCH DIAMETER) HOLE COUNTERSINK 100 x 0.18 DIAMETER MS20426AD3-4A RIVET (2 REQUIRED) BL NUMBER 30 (0.128 INCH DIAMETER) HOLE MS20470AD4-4A5 RIVET (2 REQUIRED) NUMBER 10 (0.193 INCH DIAMETER) HOLE MS21047L3 NUTPLATE STRAP FWD BULKHEAD BULKHEAD H 0.25
17 Page 17 Figure 1. Shoulder Harness Installation (Sheet 7) DETAIL I PASSENGER HARNESS INSTALLATION THRU (LEFT SIDE SHOWN, RIGHT SIDE OPPOSITE) EXISTING BRACKET MS SCREW NAS1149F0332P WASHER (2 REQUIRED) S HARNESS HOOK MS21042L3 NUT REMOVE AND DISCARD EXISTING BOLT AN43B4A BOLT REAR UPHOLSTERY PANEL TRIM AS REQUIRED TO CLEAR BOLT MS21044N4 NUT SPRING BL 0.00 NAS1149F0332P WASHER
18 Page 18 Figure 1. Shoulder Harness Installation (Sheet 8) DETAIL J LOOKING OUTBOARD AT PASSENGER SHOULDER HARNESS INSTALLATION (RIGHT SIDE SHOWN, LEFT SIDE OPPOSITE) THRU , AND 634 FWD UP (LEFT) (RIGHT) PLATE STIFFENER WL USE EXISTING PILOT HOLES IN PLATE DRILL TO NUMBER 30 (0.128 INCH DIAMETER) HOLE. INSTALL S RIVET (18 REQUIRED). C C VIEW C-C LOOKING AFT AT PASSENGER SHOULDER HARNESS INSTALLATION (RIGHT SIDE SHOWN, LEFT SIDE OPPOSITE) OUTBD UP NUTPLATE SKIN (LEFT) (RIGHT) PLATE STIFFENER
19 Page 19 Figure 1. Shoulder Harness Installation (Sheet 9) DETAIL K COCKPIT HARNESS INSTALLATION thru , 631, and 634 (RIGHT SIDE SHOWN, LEFT SIDE OPPOSITE) SPACER DETAIL M thru , 634 (RIGHT SIDE SHOWN, LEFT SIDE OPPOSITE) DETAIL L thru , and 631 (RIGHT SIDE SHOWN, LEFT SIDE OPPOSITE) COVER HARNESS FWD UP L M NAS1149F0663P WASHER (2 REQUIRED) NAS43HT4-22 SPACER NAS1149F0463P WASHER SPACER COVER NAS464P4A12 BOLT HARNESS NAS1149F0663P WASHER (2 REQUIRED) NAS43HT4-22 SPACER NAS464P4A13 OR NAS464P4A14 BOLT
20 Page 20 Figure 1. Shoulder Harness Installation (Sheet 10) DETAIL N PASSENGER HARNESS INSTALLATION THRU , 634, 675 R THRU R F THRU F FR THRU FR (RIGHT SIDE SHOWN, LEFT SIDE OPPOSITE) HARNESS S SPACER DETAIL O (LEFT SIDE SHOWN, RIGHT SIDE OPPOSITE) MOLDING WINDOW LETTER F (0.257 INCH DIAMETER) HOLE TO MATCH EXISTING NUTPLATE 4.50 DETAIL P THRU , 634 (RIGHT SIDE SHOWN, LEFT SIDE OPPOSITE) DETAIL Q THRU , 675 R THRU R F THRU F FR THRU FR (RIGHT SIDE SHOWN, LEFT SIDE OPPOSITE) COVER NAS464P4A12 BOLT HARNESS NAS1149F0663P WASHER (2 REQUIRED) NAS43HT4-22 SPACER COVER NAS464P4A8 OR NAS464P4A10 BOLT FWD UP P Q O P Q HARNESS NAS1149F0663P WASHER (2 REQUIRED) NAS43HT4-22 SPACER NAS1149F0463P WASHER
21 Page 21 Figure 2. Seat Attachment Installation (Sheet 1 of 3) A B C DETAIL A COCKPIT INBOARD AND OUTBOARD SEAT BELT ATTACHMENT (LEFT SIDE SHOWN, RIGHT SIDE OPPOSITE) BOLT S HARNESS SPACER SEAT FITTING WASHER MS21042L4 NUT SPACER MS21042L4 NUT DETAIL B PASSENGER OUTBOARD SEAT BELT ATTACHMENT (LEFT SIDE SHOWN, RIGHT SIDE OPPOSITE) BOLT HARNESS D COCKPIT AND PASSENGER SEAT BELT ATTACHMENT THRU SHOWN OTHER SIMILAR
22 Page 22 Figure 2. Seat Attachment Installation (Sheet 2) S HARNESS MS21042L4 NUT BOLT DETAIL C PASSENGER INBOARD SEAT BELT ATTACHMENT THRU AIRPLANE SERIALS THRU , 613, 631 ARE SIMILAR DETAIL D PASSENGER INBOARD SEAT BELT ATTACHMENT R THRU R FR THRU FR AN3-4A BOLT NAS43HT4-11 SPACER BOLT WASHER LATCH NUTPLATE MS21042L4 NUT NAS1149F0432P WASHER HARNESS NAS1149F0432P WASHER SPACER
23 Page 23 Figure 2. Seat Attachment Installation (Sheet 3) DETAIL E PASSENGER INBOARD SEAT BELT ATTACHMENT THRU , 634 AIRPLANE SERIALS THRU , 675 AND F THRU F ARE SIMILAR HARNESS MS21042L4 NUT BOLT SPACER DETAIL F PASSENGER INBOARD SEAT BELT ATTACHMENT THRU F THRU F BOLT MS21042L4 NUT SPACER HARNESS
The engine cowling installation and firewall should be inspected and modified as specified in this Service Bulletin.
Single Engine Service Bulletin August 25, 2008 TITLE ENGINE COWLING ALIGNMENT INSPECTION AND MODIFICATION EFFECTIVITY Model Serial Numbers 172R 17280001 thru 17280724 172S 172S8001 thru 172S8201 REASON
More informationSingle Engine MODIFICATION KIT
Single Engine MODIFICATION KIT TITLE SECURITY LOCK INSTALLATION EFFECTIVITY Model Serial Numbers 172R 17280001 and On 172S 172S8001 and On 182S 18280001 thru 18280944 182T 18280945 and On T182T T18208001
More informationMODIFICATION KIT. Serial Numbers 300 (LC40-550FG) thru (LC42-550FG) thru (LC41-550FG) thru
Single Engine MODIFICATION KIT MK400-71-01 TITLE ENGINE OIL COOLER WINTERIZATION MODIFICATION EFFECTIVITY Model Serial Numbers 300 (LC40-550FG) 40004 thru 40079 350 (LC42-550FG) 42001 thru 421018 400 (LC41-550FG)
More informationEFFECTIVITY Serial Numbers thru , 698
Conquest TITLE AILERON HINGE BRACKET REPLACEMENT EFFECTIVITY Model Serial Numbers 441 441-0001 thru 441-0349, 698 DESCRIPTION To install stainless-steel aileron hinge brackets as a replacement for aluminum
More informationFAA approval has been obtained on technical data in this publication that affects airplane type design.
Single Engine Service Bulletin January 28, 2008 TITLE ENGINE COWLING ALIGNMENT INSPECTION AND MODIFICATION EFFECTIVITY Model Serial Numbers 172R 17280725 thru 17281262 172S 172S8202 thru 172S10006 REASON
More informationSingle Engine. Service Bulletin TITLE ENGINE MOUNT BRACKET INSPECTION
Single Engine Service Bulletin April 16, 2007 TITLE ENGINE MOUNT BRACKET INSPECTION EFFECTIVITY Model Year Serial Numbers 172 1956 thru 1959 28000 thru 29999 172 1956 thru 1959 36000 thru 36999 172 1956
More informationSERVICE KIT. February 8, 1980 Revision C - April 16, 1999 Page 1 of 24
, TITLE WING FRONT SPAR LOWER CAP MODIFICATION EFFECTIVITY MODEL YEAR SERIAL NUMBERS 401 1967/1968 401-0001 thru 401-0322 401A 1969 401A0001 thru 401A0132 401B 1970/1971 401B0001 thru 401B0121 401B 1972
More informationNOTE. KI & KI Revision H
KI-179-5 & KI-179-7 R22-series Kannad AF Integra ELT Installation Kit Instructions For R22 helicopters without ELTs or if replacing previously installed Pointer 3000-10 or 4000-10 ELT (RHC Inst l) NOTE
More informationROLL BAR FRAME 2 PLACES F-1231A-FL ROLL BAR FRAME F-1231C INBOARD F-1231B OUTBOARD ROLL BAR STRAP BAGGAGE BULKHEAD
SECTION 24iS/U: ROLLOVER F-1231A-FR ROLL BAR FRAME VAN'S AIRCRAFT, INC. F-1231A-AR ROLL BAR FRAME STRUCTURE F-1231E ROLL BAR SPLICE PLATE 2 PLACES F-1232A ROLL BAR BRACE F-01254-R-1 SUPPORT FRAME & F-01207
More informationPlease replace any copy of SEB07-2 with the attached copy of SEB07-2 Revision 1 which is printed in its entirety.
Revision Transmittal May 14, 2007 TO: Cessna Distributors, Single Engine Service Stations and CPC's SUBJECT: Single Engine Service Bulletin SEB07-2 Revision 1: Engine Mount Bracket Inspection. REASON FOR
More informationPage REV 1: Added "Step 4: Bend the tabs on the wiring channel to match the slant of the F L & -R Tunnel Sides."
14401 Keil Road NE, Aurora, Oregon, USA 97002 PHONE 503-678-6545 FAX 503-678-6560 www.vansaircraft.com info@vansaircraft.com Service Letters and Bulletins: www.vansaircraft.com/public/service.htm REVISION
More informationZODIAC 601 XL. Trim the outboard corner of the front flange of the center spar 6W4-1. Corner should not touch the side of the cabin floor skin 6B10-1.
Trim the outboard corner of the front flange of the center spar 6W4-1. Corner should not touch the side of the cabin floor skin 6B10-1. Tape the side skins to the cabin floor skin (area in front of the
More informationSERVICE KIT. TITLE McCAULEY 2A34C203/90DCA-2 TWO BLADED THREADLESS PROPELLER INSTALLATION
TITLE McCAULEY 2A34C203/90DCA-2 TWO BLADED THREADLESS PROPELLER INSTALLATION EFFECTIVITY: The following airplanes that are in a landplane, ski plane, seaplane, or amphibian configuration. MODEL SERIAL
More informationSERVICE BULLETIN SB
TITLE LIGHTS - LED TAIL POSITION LIGHT INSTALLATION EFFECTIVITY MODEL UNIT NUMBERS 500 (Citation) -0001 thru -0349 with SB500-33-07 incorporated 500 (Citation I) -0350 thru -0528 with SB500-33-07 incorporated,
More informationKI (14V) & KI (28V) R44
KI-228-1 (14V) & KI-228-2 (28V) R44 Radar Altimeter Installation Kit Instructions For B050 upper console only; includes parts for In-Console and Above-Console installations. NOTE Visit www.robinsonheli.com
More information1) Page: REV 5: Changed depiction to show added hardware and T-01220
REVISION DESCRIPTION: 1) Page: 37-01 REV 5: Changed depiction to show added hardware and T-01220 Page: 37-02 REV 4: Added Figure 3 depicting Separating the T-01220 Doublers. Figure 4 was Figure 3. Added
More informationPage: REV 1: In Step 4 "a minimum of 1/16 [1.6 mm] gap" was "an approximately 1/16 [1.6 mm] gap."
14401 Keil Road NE, Aurora, Oregon, USA 97002 PHONE 503-678-6545 FAX 503-678-6560 www.vansaircraft.com info@vansaircraft.com Service Letters and Bulletins: www.vansaircraft.com/public/service.htm REVISION
More informationPage: MEMO: In NOTE before Step 5, "Whenever possible, ream using a drill press..." was "Always ream using a drill press...".
14401 Keil Road NE, Aurora, Oregon, USA 97002 PHONE 503-678-6545 FAX 503-678-6560 www.vansaircraft.com info@vansaircraft.com Service Letters and Bulletins: www.vansaircraft.com/public/service.htm REVISION
More informationaileron rib inspection
Piper Aircraft, Inc. 2926 Piper Drive Vero Beach, Florida, U.S.A. 32960 SERVICE NO. 1216B BULLETIN PIPER CONSIDERS COMPLIANCE MANDATORY Date: September 5, 2012 (S) Service Bulletin 1216B supersedes Service
More informationSERVICE INSTRUCTION SI Revision 1
SERVICE INSTRUCTION SI-25-02 Revision 1 TITLE: Aft Seats Inertia Reel Harness Installation (Mod 1229) SUBJECT / REASON / DESCRIPTION: The FBA-2C1 and FBA-2C2 aircraft are equipped with three individual
More informationSERVICE BULLETIN. Citation SB TITLE DOORS - WIDE DOOR INSTALLATION MODIFICATION
TITLE DOORS - WIDE DOOR INSTALLATION MODIFICATION EFFECTIVITY MODEL SERIAL NUMBERS 560 (Citation Encore) -0539 thru -0707 560 (Citation Encore+) -0751 thru -0815 NOTE: This modification may only be accomplished
More information36-01 REV 1: Updated figure to depict current F Bellcrank configuration.
REVISION DESCRIPTION: 36-01 REV 1: Updated figure to depict current F-00067 Bellcrank configuration. 36-06 REV 1: Updated Figure 1 and Figure 2 to depict current F-00067 Bellcrank configuration. 36-07
More informationREVISION DESCRIPTION:
14401 Keil Road NE, Aurora, Oregon, USA 97002 PHONE 503-678-6545 FAX 503-678-6560 www.vansaircraft.com info@vansaircraft.com Service Letters and Bulletins: www.vansaircraft.com/public/service.htm REVISION
More informationService Bulletin. SB-GA Issue 1. Subject: Horizontal Stabiliser Attachment Area Inspection and Reinforcement. Applicability: Amendments:
PO Box 881, Morwell, Victoria 3840, Australia Ph + 61 (0) 3 5172 1200 Fax + 61 (0) 3 5172 1201 www.mahindraaerospace.com Service Bulletin SB-GA8-2016-163 Issue 1 OPTIONAL Subject: Horizontal Stabiliser
More informationSection 75-ZA-3 Fin & Rudder Cable Fairing Installation
Section 75-ZA-3 Fin & Rudder Cable Fairing Installation This manual has been prepared for installation of the Fin and Fairings. This photo assembly manual is intended as a supplement to the drawings. If
More informationAirworthiness Directive Schedule
Airworthiness Directive Schedule Aeroplanes Cessna 120 26 November 2015 Notes 1. This AD schedule is applicable to Cessna 120 aircraft manufactured under Federal Aviation Administration (FAA) Type Certificate
More informationSERVICE BULLETIN REVISION TRANSMITTAL
REVISION TRANSMITTAL REASON This sheet transmits Revision 1 to, which: A. Adds instructions and parts to change the Pulselite controller for airplanes with the Pulselite feature. NOTE: This revision replaces
More informationREVISION DESCRIPTION:
14401 Keil Road NE, Aurora, Oregon, USA 97002 PHONE 503-678-6545 FAX 503-678-6560 www.vansaircraft.com info@vansaircraft.com Service Letters and Bulletins: www.vansaircraft.com/public/service.htm REVISION
More informationPage: MEMO: In Figure 3, "2X 1 3/32 [27.78 mm]" was "2X 1 3/32 [2.75 mm]"
14401 Keil Road NE, Aurora, Oregon, USA 97002 PHONE 503-678-6545 FAX 503-678-6560 www.vansaircraft.com info@vansaircraft.com Service Letters and Bulletins: www.vansaircraft.com/public/service.htm REVISION
More informationATTACHMENT. Orders for the required parts listed below must be placed by using this form only. Service Station/Company Code: Company Name:
Single Engine ATTACHMENT CREW SEAT RECLINE MODIFICATION SB04-25-01 Revision 4 Orders for the required parts listed below must be placed by using this form only. NOTE: All web orders for these kits/parts
More informationSERVICE BULLETIN REVISION
Revision 1 REVISION TRANSMITTAL SHEET This sheet transmits Revision 1 to. A. Adds Sheet 4 to Figure 1. B. Adds instructions to make the cutouts in the stiffener on the upper engine cowl larger. NOTE: This
More informationperformance S T O L Installation Instructions Manual No. PSTOL-013 Double Slotted Flaps for Piper PA-18 Series Aircraft
performance S T O L Installation Instructions Manual No. PSTOL-013 Double Slotted Flaps for Piper PA-18 Series Aircraft 1 This Page Intentionally Left Blank 2 Record of Revisions Rev Level Date Page By
More informationFAA approval has been obtained on technical data in this publication that affects airplane type design.
Caravan Service Bulletin July 20, 2010 TITLE RIGHT INBOARD FLAP BELL CRANK BEARING INSPECTION / REPLACEMENT EFFECTIVITY The airplanes that follow that have had part number S3952-5 Bearing(s) installed
More informationSECTION 26iS/U: FUEL TANK VAN'S AIRCRAFT, INC. T R OUTBOARD RIB IE-00001X MECHANICAL FUEL GAUGE T R INBOARD RIB T R
VAN'S AIRCRAFT, INC. SECTION 26iS/U: IE-00001X MECHANICAL FUEL GAUGE T-01222-R OUTBOARD RIB FUEL TANK T-01223-R INBOARD RIB T-01228 RETURN LINE BRACKET T-01224-R INBOARD RIB T-01229 INLET ASSEMBLY T-01223-L
More informationTECHNICAL BULLETIN May 2013 Revision A, 11 July 2013 SUBJECT: TAIL ROTOR GEARBOX 3 PIECE FAIRING, MODIFICATION OF
TECHNICAL BULLETIN 206-13-205 24 May 2013 Revision A, 11 July 2013 MODEL AFFECTED: 206A/B SUBJECT: TAIL ROTOR GEARBOX 3 PIECE FAIRING, MODIFICATION OF HELICOPTERS AFFECTED: Serial number 004 through 1251.
More informationInstallation Instructions
Installation Instructions Manual No. PSTOL-013 Performance STOL Double Slotted Flaps for Piper PA-18 Series Aircraft 1 This Page Intentionally Left Blank 2 Record of Revisions Rev Level Date Page By Explanation
More informationCHAPTER 15 FURNISHINGS. Section Title Page
CHAPTER 15 FURNISHINGS Section Title Page 15.000 Description..................................... 15.1 15.100 Seat Harnesses................................... 15.3 15.110 Four-Point Harness Assembly.................
More informationSERVICE BULLETIN REVISION TRANSMITTAL
REVISION TRANSMITTAL This sheet transmits Revision 2 to, which: A. Adds the CI401-460 GPS Antenna to Step 10A and Step 10B. B. Adds the CI401-460 GPS Antenna to Figure 5. C. Adds the CI401-460 GPS Antenna
More informationService Bulletin. ATA 27-00: Flight Controls Rudder-Aileron Interconnect Modification
Service Bulletin Issued: 09 May 2007 Models SR20 and SR22 ATA 27-00: Flight Controls Rudder-Aileron Interconnect Modification COMPLIANCE Mandatory: Accomplish this Service Bulletin within 25 Flight Hours
More informationTECHNICAL BULLETIN May 2013 SUBJECT: TAIL ROTOR GEARBOX 3 PIECE FAIRING, MODIFICATION OF
TECHNICAL BULLETIN 206-13-205 24 May 2013 MODEL AFFECTED: 206A/B SUBJECT: TAIL ROTOR GEARBOX 3 PIECE FAIRING, MODIFICATION OF HELICOPTERS AFFECTED: Serial number 004 through 1251. COMPLIANCE: At customer
More informationSERVICE LETTER. Model 1A162 Propeller, and the McCauley Fixed Pitch Propeller Service Manual.
September 4, 2009 TITLE MODEL 1A162/TCD6754 PROPELLER SERVICE INFORMATION UPDATE TO: FAA-Approved Propeller Repair Stations, Aircraft Manufacturers, Owners and Operators EFFECTIVITY Model 1A162 Propeller,
More informationJune 16, 1947 OPTIONAL CHANGE SERVICE BULLETIN NO. 17 INSTALLATION STEERABLE TAIL WHEEL. (Includes Supplement 1 and Supplement 2)
SERVICE BULLETIN REPUBLIC AVIATION CORPORATION FARMINGDALE, LONG ISLAND, NEW YORK SERVICE DEPARTMENT June 16, 1947 OPTIONAL CHANGE SERVICE BULLETIN NO. 17 INSTALLATION STEERABLE TAIL WHEEL (Includes Supplement
More informationREVISION DESCRIPTION:
14401 Keil Road NE, Aurora, Oregon, USA 97002 PHONE 503-678-6545 FAX 503-678-6560 www.vansaircraft.com info@vansaircraft.com Service Letters and Bulletins: www.vansaircraft.com/public/service.htm REVISION
More informationSECTION 22: FWD LOWER FUSELAGE VAN'S AIRCRAFT, INC F-1257 RUDDER PEDAL SUPPORT CHANNEL, 4 PLACES WD-1204 ENGINE MOUNT BRACKET, 2 PLACES
SECTION 22: F-1257 RUDDER PEDAL SUPPORT CHANNEL, WD-1204 ENGINE MOUNT BRACKET, VAN'S AIRCRAFT, INC. FWD LOWER F-1201B FIREWALL SHELF FIREWALL BOTTOM FUSELAGE TUNNEL RIB F-1271-R FWD FUSE CORNER SKIN F-1288
More informationSAMPLE BLUE STAR CONVERSION INSTALLATION OF CONTINENTAL IO-470-C OR IO-470-N BEECH MODELS THROUGH F-33 LWS STC # SA5527SW REVISION 5
BLUE STAR CONVERSION INSTALLATION OF CONTINENTAL IO-470-C OR IO-470-N BEECH MODELS 35-33 THROUGH F-33 LWS 470-33 STC # SA5527SW REVISION 5 FEBRUARY 5, 1996 BLUE STAR CONVERSION TABLE OF CONTENTS PAGE DESCRIPTION
More informationFUSELAGE CABIN ASSEMBLY
SECTION 3 Cabin Frame Ref Dwg 8FC-3 The Top of the Cabin Frame is level The distance between the front and rear wing attachment to fit the wings SECTION 3 - Page 1 of 10 CABIN FRAME 8F18-1 The TOP TUBES
More informationINSTRUCTIONS FOR CONTINUED AIRWORTHINESS AND EQUIPMENT MAINTENANCE MANUAL FOR Bell 212/ 412 CARGO NET/TROOP SEAT
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS FOR STC No. SR09485RC ON BELL 212/412 REPORT NUMBER HF-412-ICA-CARGO NET-01 HELIFAB 1318 SMEDE HWY. BROUSSARD, LA 70518 THIS MANUAL IS PREPARED TO PROVIDE INFORMATION,
More informationThe parts that follow are available from Cessna Parts Distribution through an appropriate Cessna Service Station.
Service Newsletter June 15, 2010 TITLE MECHANICAL AIR CONDITIONER COMPRESSOR DRIVER SHEAVE / PULLEY ALIGNMENT TO Cessna Distributors and Single Engine Service Stations MODELS AFFECTED The following airplanes
More informationINSTALLATION INSTRUCTIONS
INSTALLATION INSTRUCTIONS Hidden Winch Mount For 2008 Ford Super Duty Kit 78105 Your safety, and the safety of others, is very important. To help you make informed decisions about safety, we have provided
More informationVAN'S AIRCRAFT, INC. SECTION 40: LIGHTING
SECTION 40: LIGHTING RIGHT WING ASSEMBLY W-00014 LENS LN-200-1 WING TIP NAV/POSITION/ STROBE LIGHT LL-200 LANDING LIGHT W-1223E LENS BACKING STRIP, W-1222-R EXTENSION W-1223B-L LANDING LIGHT RIB NOTE:
More informationSERVICE BULLETIN TITLE AIR CONDITIONING - R134A AIR CONDITIONER SYSTEM INSTALLATION FOR AIRPLANES EQUIPPED WITH G1000 AND 867 SHP ENGINE
TITLE AIR CONDITIONING - R134A AIR CONDITIONER SYSTEM INSTALLATION FOR AIRPLANES EQUIPPED WITH G1000 AND 867 SHP ENGINE EFFECTIVITY DESCRIPTION MODEL 208B SERIAL NUMBERS 208B5000 and On To provide parts
More informationPage: REV 3: Add drill and tap information to Figure 4 DRILL #3, TAP 1/4-28 BOTH ENDS.
REVISION DESCRIPTION: 1) Page: 32-03 MEMO: Step 4 should not be bold. Fix WD-1213 callout in Figure 3. Page: 32-04 REV 3: Add drill and tap information to Figure 4 DRILL #3, TAP 1/4-28 BOTH ENDS. Add make
More informationSection 13. Tail Rotor Drive. RotorWay International A600 TALON Construction Manual. Section 13. Page A
RotorWay International Page A Tail Rotor Drive Procedures covered in this section: Install driveshafts and gearboxes; install drive belt and tensioner; fabricate and install tail rotor pitch actuator arms;
More informationSERVICE LETTER REVISION TRANSMITTAL
REVISION TRANSMITTAL TO: Cessna Distributors, Multi-Engine Authorized Service Facilities, and CPC's SUBJECT: Multi-Engine Service Letter Revision 1: Hydraulic Power Pack Inspection REASON To add a coarse-threaded
More informationSERVICE LETTER REVISION TRANSMITTAL
REVISION TRANSMITTAL This sheet transmits Revision 1 to, which: A. Changes the Inspection warranty time to 0.2 from 3.0. B. Adds the note in the LABOR HOURS section. C. Adds the QR Code and internet address
More informationSERVICE BULLETIN REVISION TRANSMITTAL
REVISION TRANSMITTAL This sheet transmits Revision 2 to, which: A. Adds the reference to Figure 7, Sheet 1 and Sheet 2 to Step 10D. B. Adds Step 10D(7). C. Removes the After Modification view for PN343
More informationA bar next to the text in the right hand margin indicates that the text has been changed as a result of the most recent document revision.
Cessna Aircraft Company Page 1 REVISIONS Rev Date By Approved By - 30 November 2009 Jay York A 18 March 2010 Jay York B 30 March 2010 Jay York ECR 067497 Section ALL Description Initial Release NOTE: A
More informationSERVICE LETTER. Multi-engine TITLE NACELLES/PYLONS - NACELLE FITTING INSPECTION EFFECTIVITY
TITLE NACELLES/PYLONS - NACELLE FITTING INSPECTION EFFECTIVITY REASON MODEL 402C 414A SERIAL NUMBERS 402C0001 thru 402C1020 that have SK402-47 - Lower Front Wing Spar Cap Inspection/Modification (Original
More informationThis Service Bulletin is applicable only to airplanes equipped with placards that are written in English.
Caravan Service Bulletin June 25, 2007 TITLE FUEL CAPACITY PLACARD REPLACEMENT EFFECTIVITY This Service Bulletin is applicable only to airplanes equipped with placards that are written in English. The
More informationSingle Engine. Service Bulletin TITLE ELEVATOR TRIM TAB ACTUATOR ASSEMBLY INSPECTION EFFECTIVITY. Group A airplanes: Serial Numbers
Single Engine Service Bulletin March 12, 2007 TITLE ELEVATOR TRIM TAB ACTUATOR ASSEMBLY INSPECTION EFFECTIVITY Group A airplanes: Model Serial Numbers 172R 17281353 thru 17281364, 17281369 thru 17281372
More informationSECTION 47: COWL BAFFLE VAN'S AIRCRAFT, INC. CB RIGHT AFT BAFFLE CB CYLINDER 3 BAFFLE VA-187 4" FLANGED DUCT
SECTION 47: CB-00014 CYLINDER 3 BAFFLE CB-00015 RIGHT AFT BAFFLE VA-187 4" FLANGED DUCT COWL BAFFLE CB-00031-R MAGNETO COOLING TUBE CB-00016 AFT CENTER BRACKET CB-00017 LEFT AFT BAFFLE CB-00013 RIGHT AIR
More informationREVISION LIST CHAPTER 15: SEATS AND SEAT BELTS
REVISION LIST CHAPTER 15: SEATS AND SEAT BELTS The following list of revisions will allow you to update the Legacy construction manual chapter listed above. Under the Action column, R&R directs you to
More informationSUBJECT: FUEL SYSTEM FLOW SWITCHES, P/N , , -003, -101 AND -103, REPLACEMENT OF
ALERT SERVICE BULLETIN 206L-88-52 10 June 1988 Revision A, 26 March 2013 MODEL AFFECTED: 206L and 206L-1 SUBJECT: FUEL SYSTEM FLOW SWITCHES, P/N 206-063- 635-001, 206-064-601-001, -003, -101 AND -103,
More informationAyres service bulletin Corporation
Ayres service bulletin Corporation No. SB-AG-37 P.O. BOX 3090 ONE AYRES WAY ALBANY, GEORGIA 31706-3090 PHONE 229/883-1440 FAX 229/439-9790 Service Bulletin No. SB-AG-37 Page 1 of 12 Approval: FAA Approved
More informationMANPOWER REQUIREMENTS
CIRRUS SF5X Service Bulletin Number: Issued: Revised: 09 Aug 208 SNS SUBJECT: 25-0 CABIN - Armrest Installation. COMPLIANCE Optional: Accomplishment of this Service Bulletin is at the owner s option. This
More informationNEW PRODUCT RELEASE. PRODUCT/KIT NAME: 12 Stabilator Tip Fairing Kit
14401 Keil Road NE, Aurora, Oregon, USA 97002 PHONE 503-678-6545 FAX 503-678-6560 www.vansaircraft.com info@vansaircraft.com Service Letters and Bulletins: www.vansaircraft.com/public/service.htm NEW PRODUCT
More informationSERVICE BULLETIN THIS BULLETIN IS FAA APPROVED FOR ENGINEERING DESIGN
MOONEY INTERNATIONAL CORPORATION SERVICE BULLETIN 165 Al Mooney Road North Kerrville, Texas 78028 THIS BULLETIN IS FAA APPROVED FOR ENGINEERING DESIGN SERVICE BULLETIN M20-318 Date: June 2, 2014 SUBJECT:
More informationR66 Aux Fuel Tank Installation Relay Upgrade Kit Instructions (To comply with R66 Service Bulletin SB-24) NOTE
R66 Aux Fuel Tank Installation Relay Upgrade Kit Instructions (To comply with R66 Service Bulletin SB-24) NOTE Visit www.robinsonheli.com to verify kit instructions are current revision. Review instructions
More informationF-1202D-L PANEL ATTACH STRIP F L UPPER FWD FUSELAGE SKIN RIB F CABIN EGRESS HANDLE F-1240B COVER PLATE
SECTION 29iS/U: F-1202D-L PANEL ATTACH STRIP F-01240-1 UPPER FORWARD FUSELAGE SKIN (SHOWN TRANSPARENT) VAN'S AIRCRAFT, INC. FWD UPPER FUSELAGE F-00078 CABIN EGRESS HANDLE F-00077-L UPPER FWD FUSELAGE SKIN
More informationFLAP, AILERON, FLAP/FUSELAGE AND STABILATOR GAP SEAL INSTALLATION AND MAINTENANCE MANUAL
FLAP, AILERON, FLAP/FUSELAGE AND STABILATOR GAP SEAL INSTALLATION AND MAINTENANCE MANUAL Aircraft Eligibility: Piper PA-28-151, PA-28-161, PA-28-181, PA-28-201T, PA-28-236, PA- 28R-201, PA-28R-201T, PA-28RT-201,
More information2000 SERIES SPEEDBRAKE INSTALLATION MANUAL STC NO. SA2602NM
INSTALLATION REPORT NO. 08062 Serial Number PRECISE FLIGHT, INC. 800-547-2558 2000 SERIES SPEEDBRAKE INSTALLATION MANUAL CESSNA 210G, T210G, 210H, 210J, 210K, T210J, 210L, T210L, 210M, T210M, 210N, P210N,
More informationInstallation Instructions
1999-2010 GM 2500-3500 HD 18K Industry Standard SuperRail Custom Mounting Kit #2326 Industry Standard Super 5 th #1900 Gross Trailer Weight (Maximum) 16,000 lbs. Vertical Load Weight (Max. Pin Weight)
More informationMustang Shaker
2005-2009 Mustang Shaker CDC #110050 ( 05/ 06) or 0711-7000-01 ( 07/ 09) Component Check List: Quantity/Description Part # CDC Installer 1 - Engine Cover Assembly 114050 1 - Aluminum Shaker Scoop 183020
More informationSERVICE BULLETIN. EFFECTIVITY SERIAL NUMBERS 680 (Citation Sovereign) thru (Citation Sovereign+) thru -0549
TITLE DOORS - CABIN DOOR SUPPORT STRUT FITTING MODIFICATION EFFECTIVITY MODEL SERIAL NUMBERS 680 (Citation Sovereign) -0001 thru -0349 680 (Citation Sovereign+) -0501 thru -0549 REASON The equivalent of
More informationREVISION LIST CHAPTER 6: AILERON CONTROLS
REVISION LIST CHAPTER 6: The following list of revisions will allow you to update the Legacy construction manual chapter listed above. Under the Action column, R&R directs you to remove and replace the
More informationRevision Transmittal Sheet
b 2 APPROVED WHITE IN LEARJET 23/24/25, 28/29, 35/36 RT 0980 Revision Transmittal Sheet This page transmits Revision 1 to, Replacement of Air Conditioning Evaporator Assembly. Rework: No rework is required
More informationSUBJECT: Single Engine Service Bulletin SB Revision 1: Cosmetic Window Repair
Revision Transmittal TO: Cessna Distributors, Single Engine Service Stations SUBJECT: Single Engine Service Bulletin Revision 1: Cosmetic Window Repair REASON FOR REVISION To revise the Compliance section
More informationPage REV 1: Added 'Step 2: See the "REMOVE THIS TAB, BOTH SIDES" callout near Detail A. Modify four SB375-4 Snap Bushings as shown.
14401 Keil Road NE, Aurora, Oregon, USA 97002 PHONE 503-678-6545 FAX 503-678-6560 www.vansaircraft.com info@vansaircraft.com Service Letters and Bulletins: www.vansaircraft.com/public/service.htm REVISION
More informationEXPRESS ASSEMBLY MANUAL SECTION 3 F5-RG/FT WING ASSEMBLY. Procedure 3.050A INSTALLATION OF AILERON TORQUE TUBE ASSEMBLY
Procedure 3.050A INSTALLATION OF AILERON TORQUE TUBE ASSEMBLY In this procedure The aileron torque tube will be assembled and installed in the wing. Part Number Description Quantity 111-24-050 Torque Tube,
More informationREVISION DESCRIPTION: REV 2: Steps re-written for clarity REV 2: Steps re-written for clarity.
REVISION DESCRIPTION: 14-04 REV 2: Steps re-written for clarity. 14-05 REV 2: Steps re-written for clarity. SECTION 14: W-1012-L OUTBOARD W-1012-R TRIMMED OUTBOARD S W-1012-L OUTBOARD W-1025B-R FLAP HINGE
More information2000 SERIES SPEEDBRAKE INSTALLATION MANUAL MOONEY M20 SERIES & M22 STC NO. SA4342NM NOTE: READ THESE DIRECTIONS BEFORE STARTING!
INSTALLATION REPORT NO. 08059 Serial Number PRECISE FLIGHT, INC. 800-547-2558 2000 SERIES SPEEDBRAKE INSTALLATION MANUAL MOONEY M20 SERIES & M22 NOTE: READ THESE DIRECTIONS BEFORE STARTING! THIS DOCUMENT
More informationSERVICE BULLETIN SERIAL NUMBERS. The equivalent of this service bulletin has been incorporated on production airplanes and On.
TITLE FUSELAGE - TAILCONE GROUND RECEPTACLE INSTALLATION EFFECTIVITY MODEL SERIAL NUMBERS 560-0539 thru -0649 REASON The equivalent of this service bulletin has been incorporated on production airplanes
More informationREVISION DESCRIPTION:
REVISION DESCRIPTION: 14401 Keil Road NE, Aurora, Oregon, USA 97002 PHONE 503-678-6545 FAX 503-678-6560 www.vansaircraft.com info@vansaircraft.com Service Letters and Bulletins: www.vansaircraft.com/public/service.htm
More informationChapter 52 DOORS -Title
Chapter 52 DOORS 52-Title Page 1 January 23, 2012 INTENTIONALLY LEFT BLANK 52-Title Page 2 January 23, 2012 LIST OF EFFECTIVE PAGES Chapter Section Page No. Date 52 52-Title 1 January 23, 2012 2 January
More information11 - Fairings. Fairings. February XLF Page 11-1
11 - Fairings Fairings February 2003 11-XLF Page 11-1 11 - Fairings This Page Intentionally Left Blank Page 11-2 11-XLF February 2003 11 - Fairings Contents 11.0 - Chapter Preface... 11-4 11.0.1 - Parts
More informationINSTALLATION PROCEDURE, HHT WITH BULKHEAD. Vehicle prep
INSTALLATION PROCEDURE, HHT WITH BULKHEAD Vehicle prep Notice where the top will interface with the vehicle. The bulb seal on the front of the hard top will rest on the windshield frame. The doorposts
More informationService Bulletin No.: DAC Rev 0 Date Issued: 27 July 2018 Title: Installation of Diamond Flap Module and Microswitch Tray
Page: 1 of 8 1. ATA Code: 2700 2. Effectivity: Serial number C0002 to C0647. 3. General: This service bulletin allows the installation of the Diamond Aircraft Flap Control Module Unit and microswitch tray.
More informationAVIAT AIRCRAFT INC. P.O. Box South Washington Afton, WY USA Fax:
DATE: 7 February 2000 REVISION: Orig. AIRCRAFT: PITTS SPECIAL S-2C P.O. Box 1240 672 South Washington Afton, WY 83110 USA 307-886-3151 Fax: 307-885-9674 aviat@aviataircraft.com SUBJECT: Elevator Forward
More information53-40 ATTACH FITTINGS
ATTACH FITTINGS. DESCRIPTION Attach fittings are provided for attachment of the seats (Refer to -0), baggage straps (Refer to -0), rear seat harnesses (Refer to -0), cargo net straps (Refer to -0), cabin
More informationAFT MOUNTED OXYGEN SYSTEM INSTALLATION BEECHCRAFT 33, 35, 36, 55, AND 58
ENGINE TECHNOLOGIES INC. REPORT 35-4960004, REV. A, JULY 12, 2013 INSTALLATION INSTRUCTIONS FOR OXYGEN SYSTEM ON HAWKER BEECHCRAFT S35, V35, V35A, V35B, 35-C33A, E33A, 36, A36, F33A, G33, 95-55, 95-A55,
More informationSERVICE LETTER SERIAL NUMBERS. 550/ thru -0505, thru -0733, thru -0969
TITLE FUSELAGE - DORSAL FIN VANE INSPECTION EFFECTIVITY MODEL SERIAL NUMBERS 550/551-0002 thru -0505, -0550 thru -0733, -0801 thru -0969 REASON The equivalent of this service letter has been incorporated
More informationMtn View Aviation An AP Enterprises, LLC Company PO Box 31 Hubbard, OR MVA-206C10M&O. Installation Instructions
Mtn View Aviation An AP Enterprises, LLC Company PO Box 31 Hubbard, OR 97032 Installation and Instructions for Continued Airworthiness for Door Steward Cessna 206/207 - Utility Door In Accordance with
More information12.0 CONTROLS 3/3/2006. Page 1
Page 1 Page 2 SR3500 Rudder Pedal Parts List ITEM DESCRIPTION PART NUMBER QTY 1 MASTER BRAKE PEDAL RP0015 2 2 SLAVE BRAKE PEDAL RP0016 2 3 PUSH ROD RP0017 4 4 SLAVE BRAKE TORQUE TUBE RP0018 2 5 MASTER
More informationPARAVION TECHNOLOGY, INC AIRWAY AVENUE FORT COLLINS, COLORADO REPORT NO. PR-206H-900M CABIN HEATER SYSTEM INSTALLATION INSTRUCTIONS
PARAVION TECHNOLOGY, INC. 2001 AIRWAY AVENUE FORT COLLINS, COLORADO 80524 REPORT NO. CABIN HEATER SYSTEM INSTALLATION INSTRUCTIONS BELL 206A/B HELICOPTERS Page i PR- Rev. P, 04/06/09 REVISIONS REV. DATE
More informationTEMPORARY REVISION NUMBER
TEMPORARY REVISION NUMBER 7 DATED 1 DECEMBER 2011 MANUAL TITLE MANUAL NUMBER - PAPER COPY TEMPORARY REVISION NUMBER FR172 Reims Rocket 1968 Thru 1976 Service Manual D849-5-13 D849-5TR7 MANUAL DATE 15 August
More informationInstallation Instructions
DODGE 20K Industry Standard Rail Custom Mounting Kit #2740 Gross Trailer Weight (Maximum)...20,000 lbs. Vertical Load Weight (Max. Pin Weight)...5,000 lbs. SYSTEM TOW CAPACITY Please note, in order to
More information2000 SERIES SPEEDBRAKE INSTALLATION MANUAL PA28/PA32 STC # SA00762SE
INSTALLATION REPORT NO. 08067 Serial Number PRECISE FLIGHT, INC. 800-547-2558 2000 SERIES SPEEDBRAKE INSTALLATION MANUAL PA28/PA32 STC # SA00762SE NOTE: READ THESE DIRECTIONS BEFORE STARTING! CHECK FOR
More information2005+ Roll Bar (Mm5RB-20.1 to -20.6) Recommended Center punch 1/8" pilot drill 1-3/4" Hole saw 2" Hole saw
3430 Sacramento Dr., Unit D San Luis Obispo, CA 93401 Telephone: 805/544-8748 Fax: 805/544-8645 www.maximummotorsports.com 2005+ Roll Bar (Mm5RB-20.1 to -20.6) Recommended Center punch 1/8" pilot drill
More informationAirglas, Inc. Installation Instructions. MANUAL NO. LH MODEL LH4000 Ski Kit For Cessna 180 and 185 Aircraft.
Airglas, Inc. Installation Instructions MANUAL NO. LH4000-105 MODEL LH4000 Ski Kit For Cessna 180 and 185 Aircraft Cage Code 17564 This Page Intentionally Left Blank 2 P a g e REV LEVEL Initial Release
More informationSTOL CH 701. STOL CH701 cabin. Top view: Tunnel 7F11-4 between the Seats. STOL CH701 Seats
CH701 cabin Top view: Tunnel 7F11-4 between the Seats. CH701 Seats CHECK: If the Gusset 7F11-7 is supplied bent; hen it is best to install the Gusset before the Seat 7F16-1. Otherwise, install the Seat
More information