| 98-19-15 |
Fairchild |
Superseded by 07-16-3 |
| 98-19-13 |
Bell |
Replace driveshaft with airworthy driveshaft to prevent failure and loss of control. | 407 |
| 98-18-15 |
Gulfstream |
Perform a visual inspection and measure the clearance between the wiring harnesss and the crew oxygen bottle to prevent chafing of the wiring harness and possible fire. | G-V |
| 98-18-13 |
Socata |
Perform dye penetrant inspection in accordance with service bulletin to detect cracks in the main landing gear attachment bearing. | TB20,TB21 |
| 98-18-12 |
Text-Lyc |
Superseded by 03-14-3 |
| 98-18-1 |
Bell |
Supersedes 94-15-14 | Create a component history card and record the retirement index number to prevent fatigue failure of the trunnion. | 214B,214B-1,214ST |
| 98-17-15 |
Sikorsky |
Conduct visual inspection of the swashplate assembly uniball bearing retainer and replace any missing bolts. | S-76A,B,C |
| 98-17-14 |
MDHC |
Superseded by 99-8-7 |
| 98-17-11 |
Text-Lyc |
To prevent crankshaft failure determine if any repair was conducted on the engine by Nelson Balancing Service on specified dates. | Various aircraft. |
| 98-17-10 |
P&W Eng |
Check records for any engine surge entries and if so, inspect for rubbing between the second stage stator vanes and compressor rotor which can cause a in-flight shutdown of the engine. | PW530A |
| 98-17-1 |
Allied Signal |
Revised 99-21 | Supersedes 93-10-10 | To prevent possible engine fire install flexible fuel tube. | TFE731-2,-3,-4 |
| 98-16-4 |
Cessna |
Inspect inside of wings for presence of angle stiffener. Install if absent to prevent wing failure during flight. | Various 180,182,185 models |
| 98-16-3 |
Socata |
Inspect wing front attachments for cracks that can result in wing separation. | TB9,TB10 |
| 98-16-2 |
Eurocopter |
Clean and inspect tail rotor blades for cracks that can cause tail rotor blade failure. | Various SA3180,SA318,SE3130,SE313,SA315,SA316,SA319, SE3160 models |
| 98-16-18 |
Learjet |
Measure brake wear to detect any uneven brake wear condition. | 60 |
| 98-16-17 |
Cessna |
Rescission BW 2003-22 | Perform in-flight functional test of secondary horizontal stabilizer pitch trim system in accordance with SB | 750 |
| 98-15-7 |
Dassault |
Install reinforcement fitting to prevent fatigue cracking at junction of baggage door and floor. | 50 |
| 98-15-26 |
MDHC |
Supersedes 98-3-15 | Before further flight and at 25 hour intervals visually inspect main rotor for cracking in accordance with SB. | Various 369,500, |
| 98-15-18 |
Maule |
Inspect wing lift struts for corrosion to prevent failure of struts. | Various models |
| 98-15-16 |
Rotax |
Install improved fuel pump to prevent possible fuel leaks | 912F |
