Inspection of Wing Rear Attach Fitting
PIPER PA-44-180T Turbo Seminole · Service Bulletins
Overview
This document is a service bulletin for the Piper PA-44-180T Turbo Seminole, detailing inspection and maintenance procedures for the rear wing attach fittings. It addresses potential corrosion issues and the need for additional inspection access panels to facilitate maintenance.
- Corrosion may develop on the steel rear wing attach fitting due to water ingress.
- Inspection access panels are to be added for easier maintenance.
- Compliance is required at the next scheduled maintenance or within 100 hours of service.
- The bulletin includes detailed inspection and repair instructions.
- DINITROL AV 8 corrosion control compound is required for treatment.
- Drain holes must be drilled beneath each rear attach fitting.
- The document has been approved by the FAA.
- Factory participation for compliance may be available for 180 days.
Document
Source
Originally published by barteltaviation.com. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type ·
- Service Bulletins
- Year ·
- 1994
- File size ·
- 144 KB
- Publisher ·
- barteltaviation.com
- Language ·
- en
What is the Inspection of Wing Rear Attach Fitting?
The Inspection of Wing Rear Attach Fitting is a service bulletins for the PIPER PA-44-180T Turbo Seminole, dated 1994.
Where does the Inspection of Wing Rear Attach Fitting come from?
This copy of the Inspection of Wing Rear Attach Fitting was originally published by barteltaviation.com and is hosted on Sprinkle as a free, searchable reference copy.
What year was the Inspection of Wing Rear Attach Fitting published?
The Inspection of Wing Rear Attach Fitting — the PIPER PA-44-180T Turbo Seminole service bulletins on file — is dated 1994.
Most owners only have the POH. Here's the essential set for the PIPER PA-44-180T Turbo Seminole.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins on file
- Type Certificate (TCDS)
More PIPER PA-44-180T Turbo Seminolemanuals & documents
In this document
Purpose
The bulletin addresses corrosion issues on the rear wing attach fitting and the need for easier inspection access.
Instructions
Step-by-step instructions for inspecting and treating the rear wing attach fittings, including the installation of access panels.
Material Required
Lists the materials needed for compliance, including corrosion control compound and sealant.
Compliance Time
Specifies that compliance is required at the next maintenance event or within 100 hours of service.
Availability of Parts
Parts can be obtained from Piper Field Service Facilities.
Caution
Warnings regarding the cutting of baggage compartment flooring to avoid damage to underlying cables.
Safety notes
- Inspect for corrosion and treat as necessary before continued operation.
- Use care when cutting through baggage compartment flooring to avoid damaging cables.
- Ensure insulation is flame resistant and conforms to FAR part 23.853.
- Perform a leak check to identify water ingress points.
- Make appropriate logbook entries after compliance.
- Consult the Illustrated Piper Parts Catalog for replacement part numbers.
Full document text
977 DATE: December 12, 1994 (S/M) SUBJECT: I n s p e c t i o n o f W i n g R e a r A t t a ch F i t t i n g a n d A dd i t i o n o f I n s p e c t i o n A c c e s s Pa n e l s . MODELS AFFECTED: SERIAL NUMBERS AFFECTED: PA - 2 8 - 1 4 0 C h e r o ke e 2 8 - 2 0 0 0 0 t h r o u g h 2 8 - 7 7 2 5 2 9 0 PA - 2 8 - 1 5 0 / 1 6 0 / 1 8 0 C h e r o ke e 2 8 - 1 t h r o u g h 2 8 - 7 5 0 5 2 5 9 & 2 8 - E 1 3 PA - 2 8 - 1 5 1 Wa r r i o r 2 8 - 7 4 1 5 0 0 1 t h r o u g h 2 8 - 7 7 1 5 3 1 4 PA - 2 8 - 1 6 1 Wa r r i o r I I & I I I 2 8 - 7 7 1 6 0 0 1 t h r o u g h 2 8 - 8 6 1 6 0 5 7 , a n d 2 8 1 6 0 0 1 t h r o u g h 2 8 1 6 1 0 9 PA - 2 8 - 1 6 1 C a d e t 2 8 4 1 0 0 1 t h r o u g h 2 8 4 1 3 6 5 PA - 2 8 - 1 8 1 A r c h e r I I & I I I 2 8 - 7 6 9 0 0 0 1 t h r o u g h 2 8 - 8 6 9 0 0 6 2 , 2 8 9 0 0 0 1 t h r o u g h 2 8 9 0 2 0 5 PA - 2 8 - 2 3 5 C h e r o ke e 2 8 - 1 0 0 0 1 t h r o u g h 2 8 - 7 7 1 0 0 8 9 & 2 8 - E 1 1 PA - 2 8 - 2 3 6 D a ko t a 2 8 - 7 9 1 1 0 0 1 t h r o u g h 2 8 - 8 6 1 1 0 0 8 , 2 8 1 1 0 0 1 t h r o u g h 2 8 1 1 0 3 8 , 2 8 1 1 0 4 0 t h r o u g h 2 8 1 1 0 4 6 , a n d 2 8 1 1 0 4 8 PA - 2 8 - 2 0 1 T Tu r b o D a ko t a 2 8 - 7 9 2 1 0 0 1 t h r o u g h 2 8 - 7 9 2 1 0 9 5 , PA - 2 8 R - 1 8 0 A r r ow 2 8 R - 3 0 0 0 1 t h r o u g h 2 8 R - 7 1 3 0 0 1 3 PA - 2 8 R - 2 0 0 A r r ow / A r r ow I I 2 8 R - 3 5 0 0 1 t h r o u g h 2 8 R - 7 6 3 5 4 6 2 PA - 2 8 R - 2 0 1 A r r ow I I I 2 8 R - 7 7 3 7 0 0 1 t h r o u g h 2 8 R - 7 8 3 7 3 1 9 , 2 8 3 7 0 0 1 t h r o u g h 2 8 3 7 0 6 0 PA - 2 8 R - 2 0 1 T Tu r b o A r r ow I I I 2 8 R - 7 7 0 3 0 0 1 t h r o u g h 2 8 R - 7 8 0 3 3 7 4 a n d 2 8 0 3 0 0 1 t h r o u g h 2 8 0 3 0 1 2 PA - 2 8 RT- 2 0 1 A r r ow I V 2 8 R - 7 9 1 8 0 0 1 t h r o u g h 2 8 R - 8 2 1 8 0 2 6 , PA - 2 8 RT- 2 0 1 T Tu r b o A r r ow I V 2 8 R - 7 9 3 1 0 0 1 t h r o u g h 2 8 R - 8 6 3 1 0 0 5 2 8 3 1 0 0 1 t h r o u g h 2 8 3 1 0 3 8 PA - 3 2 - 2 6 0 C h e r o ke e S i x 3 2 - 1 t h r o u g h 3 2 - 7 8 0 0 0 0 8 PA - 3 2 - 3 0 0 C h e r o ke e S i x 3 0 0 3 2 - 4 0 0 0 0 t h r o u g h 3 2 - 7 9 4 0 2 9 0 PA - 3 2 - 3 0 1 S a ra t o g a 3 2 - 8 0 0 6 0 0 1 t h r o u g h 3 2 - 8 6 0 6 0 2 3 , 3 2 0 6 0 0 1 t h r o u g h 3 2 0 6 0 8 8 PA - 3 2 - 3 0 1 T Tu r b o S a ra t o g a 3 2 - 8 0 2 4 0 0 1 t h r o u g h 3 2 - 8 4 2 4 0 0 2 PA - 3 2 R - 3 0 0 L a n c e 3 2 R - 7 6 8 0 0 0 1 t h r o u g h 3 2 R - 7 8 8 0 0 6 8 PA - 3 2 RT- 3 0 0 L a n c e I I 3 2 R - 7 8 8 5 0 0 1 t h r o u g h 3 2 R - 7 9 8 5 1 0 5 PA - 3 2 RT- 3 0 0 T Tu r b o L a n c e I I 3 2 R - 7 8 8 7 0 0 1 t h r o u g h 3 2 R - 7 9 8 7 1 2 6 PA - 3 2 R - 3 0 1 S a ra t o g a S P & I I H P 3 2 R - 8 0 1 3 0 0 1 t h r o u g h 3 2 R - 8 6 1 3 0 0 6 3 2 1 3 0 0 1 t h r o u g h 3 2 1 3 0 8 0 PA - 3 2 R - 3 0 1 T Tu r b o S a ra t o g a S P 3 2 R - 8 0 2 9 0 0 1 t h r o u g h 3 2 R - 8 6 2 9 0 0 6 , 3 2 2 9 0 0 1 , 3 2 2 9 0 0 2 a n d 3 2 2 9 0 0 3 PA - 3 4 - 2 0 0 S e n e c a 3 4 - 7 2 5 0 0 0 1 t h r o u g h 3 4 - 7 4 5 0 2 2 0 PA - 3 4 - 2 0 0 T S e n e c a I I 3 4 - 7 5 7 0 0 0 1 t h r o u g h 3 4 - 8 1 7 0 0 9 2 PA - 3 4 - 2 2 0 T S e n e c a I I I & I V 3 4 - 8 1 3 3 0 0 1 t h r o u g h 3 4 - 8 6 3 3 0 3 1 , 3 4 3 3 0 0 1 t h r o u g h 3 4 3 3 0 8 8 , 3 4 4 8 0 0 1 t h r o u g h 3 4 4 8 0 4 7 PA - 4 4 - 1 8 0 S e m i n o l e 4 4 - 7 9 9 5 0 0 1 t h r o u g h 4 4 - 8 1 9 5 0 2 6 , 4 4 9 5 0 0 1 t h r o u g h 4 4 9 5 0 1 3 PA - 4 4 - 1 8 0 T Tu r b o S e m i n o l e 4 4 - 8 1 0 7 0 0 1 t h r o u g h 4 4 - 8 1 0 7 0 6 6 , 4 4 - 8 2 0 7 0 0 1 t h r o u g h 4 4 - 8 2 0 7 0 2 0 (OVER) ATA: 5740 Piper Aircraft Corporation 2926 Piper Drive Vero Beach, Florida, U.S.A. 32960 PAGE 2 OF 8 SERVICE BULLETIN NO. 977 COMPLIANCE TIME: At the next regularly scheduled maintenance event, but not to exceed the next one hundred (100) hours time in service. APPROVAL: The technical contents of this Service Bulletin have been approved by the F.A.A.. PURPOSE: Field repor ts indicate that some aircraft may be experiencing corrosion on the steel rear wing attach fitting. It appears that over time, should the seals for the windows and doors not be maintained, leaks may develop which, if not corrected, will allow an ingress of water. This water contamination will wet the insulation around the attach fitting creating a highly corrosive environment. In addition, inspection access is difficult on some early aircraft in the PA-28 Series and require that inspection access panels be installed to ease inspection in this area. This Ser vice Bulletin requires the following: Addition of two access panels to the rear floorboard; inspection to determine condition of the aircraft window and door seals and, if necessary, the corrective action needed; a one time inspection to determine the condition of the rear wing attach fittings; and addition of drain holes at the aft attach fitting area and inspection and modification of the insulation material around the affected area. INSTRUCTIONS: 1. Gain access to the left and right wing rear attach fittings. Remove seats as required. Remove interior mouldings and carpet as necessary. Consult the applicable Service Manual as required. a. For the PA-28 and 44 series aircraft, remove the rear seats and the rear floorboard. b. For the PA-32 and 34 series aircraft, remove the center seats and the center floorboard. 2. On PA-28/44 series aircraft only, remove the car pet from the baggage area floor. If two oval inspection panels are located in the floor, continue these instructions. If not install access panels per Sketch A and the instructions on page 5 prior to continuing. 3. Inspect thoroughly the left and right rear wing attach fittings for evidence of flaking paint and/or corrosion. (Flaking paint may be a symptom of hidden corrosion.) If no corrosion exists, continue with these instructions. If corrosion is superficial and there is no metal flaking and/or pitting, clean and paint
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fittings. (Use good quality aircraft primer) If corrosion is found, consult the appropriate Illustrated Piper Par ts Catalog for replacement par t numbers and obtain and install new par ts before continued operation. (See Sketch B and Instructions on page 7 for removal and re-installation.) 4. Upon completion of the inspection and after replacement or refurbishment of fittings, treat attach fitting area using DINOL AV 8 corrosion compound, Piper Part Number 89500-800. The treatment may be brushed or sprayed. 5. Inspect insulation in and around the rear fittings. If insulation is wet or matted down where it has been wet, it will be necessary to replace this insulation and it will be necessary to inspect all windows, doors and exterior panels leading to the cabin. Check door seals for deterioration, cracks and voids in adhesive. Check window seals for voids, cracks, and deterioration. Perform a leak check with water to determine where the water is entering. Cure all leak paths before continuing these instructions. Consult the appropriate Illustrated Piper Parts Catalog for replacement part numbers and obtain and install new par ts before continued operation. If sealing windows, utilize Piper Par t Number 279-058 Sealant (Bostik 1100 FS) or equivalent. If using insulation other than Piper original material, be sure that the insulation is flame resistant and conforms to FAR part 23.853. 6. If the insulation material has not been wet, or if new material is being installed, it is necessary to cut out a 6 inch clearance in the insulation in all directions around each attach fitting. 7. Locate and drill two each .191 inch drain holes, one beneath each rear attach fitting as shown on Sketch C. NOTE: When drilling from outside, use a drill stop set to 1 / 8 inch to advert possible interior damage. 8. Re-install floorboards, seats, interior panels, and other ar ticles removed in step one. Perform a functional test of any system or component that may have been interrupted or removed. 9. Make an appropriate logbook entry of compliance with this Service Bulletin. SERVICE BULLETIN NO. 977 PAGE 3 OF 8 MATERIAL REQUIRED: One (1) each, Container DINITROL AV 8 corrosion control compound, Piper Part Number 89500-800. The following are as required by inspection only: One each left and/or right Rear Wing Attach Fitting and aircraft quality insulation as required (Refer to applicable Piper Parts Catalog for Correct Part Numbers), one (1) each, Container Sealant, Piper Part Number 279-058, and the applicable number of MS20470 AD rivets per aircraft. (Sealant and rivets may be obtained locally.) AVAILABILITY OF PARTS: Your Piper Field Service Facility. EFFECTIVE DATE: This Service Bulletin is effective upon receipt. SUMMARY: Any applicable factory participation will remain in effect for a period of time not to exceed 180 days from the date of this Service Bulletin. Please contact your Factory Authorized Piper Service Facility to make arrangements for compliance with this Service Bulletin in accordance with the Compliance Time indicated and to obtain information concerning any applicable factory participation. NOTE: If you are no longer in possession of this aircraft, please forward this information to the present Owner/Operator and notify the factory of address/ownership corrections. Changes should include aircraft model, serial number, current owner's name and address. Correction/changes should be directed to: PIPER AIRCRAFT CORPORATION ATTN: Customer Service 2926 Piper Drive Vero Beach, FL 32960 PAGE 4 OF 8 SERVICE BULLETIN NO. 977 CL FORWARD AFT 14.99” 2.50” 8.48” 30° TYP 2.28” R TYP 2.00” R TYP;M 0.120” HOLE THRU N0.8 X 38 CRES TRUSS RECESSED HEAD SHEET METAL SCREWS (16 REQD.) COVER (2 REQD) PIPER P/N 62109-0 10.98” 21.80” 19.11” SKETCH A SERVICE BULLETIN NO. 977 PAGE 5 OF 8 INSTALLATION OF INSPECTION ACCESS PANELS IN PA-28/44 SERIES AIRCRAFT Baggage Compartment Inspection Holes Fabrication Procedure (Refer to Sketch A) While Sketch A shows the hole in the left side of the baggage compartment, a similar hole is also cut out in the right side baggage compartment floor. Installation will require two each inspection access covers, Piper P/N 62109-0. (If desired, these covers may be fabricated locally.) a. Layout cut lines (1) Gain access to baggage compartment. (2) Carefully remove: (a) Right side baggage compartment Royalite plastic close out panel. (b) Rear close out panel. (c) Carpeting from baggage compartment floor. (3) Determine and mark a reference center line running through baggage compartment. Refer to Figure Sketch A for measurements. (4) Measure two points 14.99 inches each side of the reference centerline. Joining these two points will form the centerlines of each inspection hole. (5) Measure two points on each side of each centerline of both holes at distances of 8.48 inches and 10.98 inches from the aft edge of the baggage compartment floor. (6) Connect the two 8.48” points and the two 10.98” points so that the resulting lines cross the centerline of each hole. (7) Using the intersection of the lines constructed in step (6) with each hole’s centerline as the center, scribe an arc having a radius of 2.00” (8) Draw a line (four lines total) tangent to the each side of the arcs constructed on step (7). (9) There should now be two ovals, like the one in Sketch A, laid out on each side of the baggage compartment floor. b. Cutting the holes. — CAUTION — Baggage compartment flooring is made of 0.025 inch thick aluminum. Use care when cutting through flooring so as not to damage cables and wiring routed below the floor. (1) Drill a 1/4 inch hole inside of, and adjacent to, one of the scribed lines layed out for each hole. (2) Using a 1/8 inch router bit, cut out the two inspection holes by following the lines layed out on each side of the baggage compartment floor. (3) Deburr each cut edge using a file or emery wheel. c. Installing covers. (1) Lay one of the 62109-0 covers over one of the inspection holes. Using the screw holes in the cover, scribe the position for the screw holes on the baggage compartment floor. (2) Drill a 0.120 inch hole in baggage compartment floor at each position layed out in step (1). (3) Attach cover to flooring with No.8 X 0.38 corrosion resistant steel sheet metal screws. (4) Repeat steps (1) through (3) on remaining hole. d. Install baggage compartment rear and side close out panels. e. Install baggage compartment floor rug. PAGE 6 OF 8 SERVICE BULLETIN NO. 977 SKETCH B REAR ATTACH FITTING REAR ATTACH FITTING AFT PA28 &PA44 SERIES PA32 &PA34 SERIES ° REMOVAL AND RE-INSTALLATION OF REAR WING ATTACH FITTINGS (IF REQUIRED) PA-28/44 SERIES (Refer to applicable Service Manual as necessary) 1. Remove electrical power from aircraft by disconnecting the battery. 2. Place jacks under wings and tail - tie down to stabilize aircraft. 3. Remove seats, removable floorboards and interior panels necessary to gain access to the rear wing attach fittings. Note: If not already installed, add inspection access panels per Sketch A. 4. On L/H side, remove bus bar assembly from spar. 5. If necessary, drill off cargo compartment floor and remove from aircraft. Note: If both fittings are to be changed, remove and replace one fitting at a time. 6. Remove bolt from wing rear spar and fuselage attach fitting. 7. Carefully drill out the rivets that attach the fitting to the spar. 8. With all the rivets removed, remove wing attach fitting from the aircraft. Discard fitting. 9. Clean and inspect the areas that were under bracket for any signs of corrosion. 10. If corrosion is found, repair or replace parts as necessary. Coat the area with primer and allow to dry. 11. If no corrosion is found, coat the area with primer. Allow time to dry. 12. Install new wing attach fitting and align rivet holes. It may be necessary to ream open the bolt hole to proper size. The hole is close tolerance and should be .3115 / .3135 (5/16) or .3745 / .3765 (3/8) depending on model and year. Replace attach fitting bolt should there be any sign of wear or corrosion. 13. Re-rivet wing attach fitting into place with appropriate fasteners. (See note at bottom of page.) 14. Install wing spar and fuselage attach fitting bolt per appropriate section of the Maintenance Manual. 15. Seal edges of attach fittings with PRC PR1422 (or equivalent) before installing interior. 16. Complete same process to the opposite side. 17. Reinstall cargo door floorboard and interior and seats. Connect battery and check for operation. PA32/34 SERIES (Refer to applicable Service Manual as necessary) Note: The many variations in this model group may require more extensive disassembly to remove the rear attach fitting. Access the job prior to determining if additional steps or additional parts may be necessary. Consult the appropriate parts catalog for additional parts as required. 1. Remove electrical power from aircraft by disconnecting the battery. 2. Place jacks under wings and tail - tie down to stabilize aircraft. Provide support for fuselage in effected area. 3. Remove seats, interior panels and center floorboard to gain access to rear wing attach fittings. 4. Remove or relocate systems components to gain access to the attach fittings. 5. Remove bolt that attaches fuselage to wing spar. 6. Carefully remove rivets, screws, inner panels, channels and brackets necessary to remove attach fitting.* Note: In order to remove some channels, it may be necessary to remove the wings. 7. Clean and inspect the areas that were under bracket for any signs of corrosion. 8. If corrosion is found, repair or replace parts as necessary. Coat the area with primer and allow to dry. 9. If no corrosion is found, coat the area with primer. Allow time to dry. 10. Install new wing attach fitting and align rivet holes. It may be necessary to ream open the bolt hole to proper size. The hole is close tolerance and should be .3115 / .3135 (5/16) or .3745 / .3765 (3/8) depending on model and year. Replace attach fitting bolt should there be any sign of wear or corrosion. 11. Re-rivet wing attach fitting into place with appropriate fasteners. (See note at bottom of page.) 12. Install wing spar and fuselage attach fitting bolt per the appropriate section of the Maintenance Manual. 13. Seal the edges of the attach fittings with PRC PR1422 (or equivalent) before installing interior. 14. Complete the same process to the opposite side. 15. Reinstall center floorboard, interior panels, and seats. Connect battery and check for operation. SERVICE BULLETIN NO. 977 PAGE 7 OF 8 Note: For hard to reach areas. it is permissible to replace the existing MS20470AD-5 rivets with Hi Lok fasteners. Use HL30-5 with HL-94 Hi Lok collars. Torque to 15 to 25 inch lbs. Observe standard practices for use of Hi Lok fasteners. PAGE 8 OF 8 SERVICE BULLETIN NO. 977 SKETCH C FROM SIDE OF FUSELAGE FUSELAGE BOTTOM SKIN LOOKING DOWN LEFT HAND SHOWN RIGHT HAND OPPOSITE TYPICAL TWIN TYPICAL SINGLE FROM THE BOTTOM OF THE AIRCRAFT LOCATE & DRILL ONE .191 INCH DRAIN HOLE EACH SIDE BENEATH EACH ATTACH FITTING USING THE MEASUREMENTS SHOWN. (LEFT & RIGHT) SET DRILL STOP TO 1/8 INCH DEPTH.