Starting the engine on a Cessna 172 - G1000

Engine start procedure in a Cessna 172 with G1000 avionics

Brandon Judson, Team Structures, discusses acceptable wear limits for flap tracks on Cessna single engine aircraft

Engine Priming and Starting Procedures: Models 182T, T182T, 172R, and 172S

This video will serve as a guide to priming and starting the engine on Models 182T, T182T, 172R, and 172S. Applicable to Lycoming-engined single engine aircraft.

LANDING GEAR - HYDRAULIC LOADING VALVE WIRE BUNDLE INSPECTION - Citation Model 560XL

EFFECTIVITY
MODEL                                                                            SERIAL NUMBERS
560XL (XLS)                     -                                             5501 thru -5830
560XL (XLS+)                  -                                             6001 thru -6150, -6152 thru -6160
The equivalent of this service letter has been incorporated on production airplanes -6161 and On.

NOTE: SL560XL-29-04 -Hydraulic Power - Hydraulic Manifold Control Valve Wire Bundle Inspection should be done in conjunction with this service letter.

REASON
To inspect the cannon plug and wire bundle for the hydraulic loading valve on the hydraulic manifold for chafing and install protective sleeving.

DESCRIPTION
This service letter provides instructions to inspect the cannon plug and wire bundle for the hydraulic
loading valve and install protective sleeving.

COMPLIANCE
MANDATORY. This service letter must be accomplished within 300 flight hours or 90 days from the date of receipt, whichever occurs first.

Using Grinding Compound or Aircraft Friction Drops to Remove Screws

Video: Using Grinding Compound or Aircraft Friction Drops to Remove Screws
ATA: 51-20	Models: All Models	Published: 11-11-2014
Dennis Kelderman, Customer Service Engineer, Team Structures demonstrates how to use a grinding compound or E-Z Grip to remove screws.

Location and Types of Standby Power Supplies for the Excel Fleet

Inform customers of the location and types of the standby power supplies based on unit numbers.
Models: 560XL, XLS, XLS+

What are the differences between Airworthiness Directives and Service Bulletins

Airworthiness Directives(AD) are issued when the FAA finds that an unsafe condition exists in a product (aircraft, aircraft engine, propeller, or appliance.) 

These AD's notify aircraft owners and operators of potential unsafe conditions and require special inspections, repairs, or alterations to correct the unsafe condition.

Service Bulletins (SB) are notices to aircraft operators from a manufacturer notifying them of a product improvement. 

Alert service bulletins are issued by the manufacturer when a condition exists that the manufacturer feels is a safety related item as opposed to just a product improvement. These SB's usually result in the FAA issuing an AD. The AD will reference the alert service bulletin as a method of compliance with the airworthiness directive. 

If a service bulletin is not an alert service bulletin or a bulletin referenced in an AD, it becomes optional and may or may not be incorporated by the operator.

Checking Brake Wear on Citation 525 Series Aircraft

This video demonstrates how to check the brake wear on Cessna Citation models 525, 525A, 525B, and 525C aircraft.

SEL-78-01R1 - Exhaust Inspection for Cracks (CESSNA MODEL T206H)

CESSNA SEL-78-01

TITLE:     EXHAUST - EXHAUST INSPECTION FOR CRACKS

EFFECTIVITY:  

MODEL SERIAL NUMBERS                         T206H T20609063 thru T20609125, T20609132 thru

                                                                                                     T20609143, T20609145

COMPLIANCE : MANDATORY. 

Until the Lycoming 40B22621 or 40B23388 Cylinder Number 3 Exhaust Pipe has no less than 400 flight hours, an Exhaust System Inspection must be accomplished as follows: (Refer to the Model 206H/T206H Maintenance Manual, Chapter 78, Exhaust System (Turbocharged) - Maintenance Practices)

1. Before further flight if one or more of the conditions that follow exist:

• Cowl Discoloration in the area of the Number 3 Exhaust Pipe

• CO alert

• Uncommanded or unexplained reduction of Manifold Absolute Pressure (MAP).

2. Within the next 25 hours or at the next scheduled oil change, whichever occurs first, and then again at each subsequent oil change not to exceed 50 hours since last inspection.

NOTE: The holder of a pilot certificate issued under 14 CFR Part 61 may perform the special inspections required by this service letter and the associated required logbook entries on any aircraft owned or operated by that pilot which is not used under part 14 CFR Part 121, 14 CFR Part 129, or 14 CFR Part 135.

If a crack is found, Lycoming Mandatory Service Bulletin No. 614A must be accomplished before

further flight.

NOTE: Lycoming Mandatory Service Bulletin No. 614A may be accomplished in lieu of the special

inspections required by this service letter.

NOTE: When the Lycoming 40B22621 or 40B23388 Cylinder Number 3 Exhaust Pipe has more than 400 flight hours or when Lycoming Mandatory Service Bulletin No. 614A has been accomplished, the special inspections required by this service letter are no longer necessary

WINGS - ACCESS PANEL INSTALLATION (Cessna Model T240)

CESSNA SEL-57-02

EFFECTIVITY

MODEL SERIAL NUMBERS                                              T240 2001 thru 2058

COMPLIANCE:     MANDATORY.

1. Special visual inspection as follows:

• During each preflight, the attachment screws for all under wing panels specified in the Accomplishment Instructions must be visually checked to make sure that they are not loose.

• If a loose screw is found, it must be tightened.

NOTE: The holder of a pilot certificate issued under 14 CFR Part 61 may perform the special inspections required by this service letter on any aircraft owned or operated by that pilot which is not used under part 14 CFR Part 121, 14 CFR Part 129, or 14 CFR Part 135.

2. The maintenance procedure specified in the Accomplishment Instructions Section of this service

letter must be accomplished within the next 100 hours of operation.

3. After the maintenance procedure specified in the Accomplishment Instructions Section of this service letter has been accomplished, the special visual inspections during preflight are no longer necessary.

WIRE INSPECTION AT THE AIR-CONDITIONING COMPRESSOR MOUNTING BRACKET (CESSNA T240)

CESSNA : SEL-24-06

TITLE: ELECTRICAL POWER - WIRE INSPECTION AT THE AIR-CONDITIONING COMPRESSOR MOUNTING BRACKET

EFFECTIVITY:   CESSNA MODEL T240 SERIAL NUMBERS T240 T24002001 thru T24002038

REASON

Cessna has determined that wires at the rear of the engine may chafe on the air-conditioning compressor mounting bracket.

DESCRIPTION

This service letter provides parts and instructions to do an inspection of wires adjacent to the air-conditioning compressor mounting bracket for damage. If damage is found, the damaged wire is replaced. Then spiral wrap and sleeving is installed over the wires in the area of the mounting bracket, and the wires are attached securely with tie straps to adjacent wiring.

COMPLIANCE

MANDATORY. This service letter must be accomplished at the next 100-hour or 12-month (annual-type) inspection.

REFERENCES

Model LC41-550FG/T240 Maintenance Manual

Shimmy Damper Servicing Check on 500-Series Citations

Video: Shimmy Damper Servicing Check on 500-Series Citations  - Models: 500, M2, 525, 525A, 525B, 550, S550, 560, 560XL

Locations of Emergency Lighting Battery Packs Model 560XL

Video: Locations of Emergency Lighting Battery Packs Model 560XL - Models: 560XL, XLS, XLS+ 

Questions, please contact:

Cessna Customer Service
+1 316-517-5800

Using a Towbarless Tug On the Citation CJ4

Video: Using a Towbarless Tug On the Citation CJ4 - Models: 525C

Preferred GPU Connection Procedures

How to Access Garmin G3000 LRU Status Information

Single Engine Climb Performance CPCalc

Mandatory Inspection Intervals and Replacement Times for Airborne Check Valve Manifolds

Airborne Air & Fuel Products

Service Letter Number: 39A

Subject: Mandatory Inspection Intervals and Replacement Times for Airborne Check Valve
Manifolds, Check Valves and Regulator Check Valve Manifolds.

Applicability:

All Airborne Check Valve Manifolds, Check Valves and Regulator Check Valve Manifolds. These valves which are listed below are typically installed on single-engine and multi-engine piston aircraft equipped with dual pneumatic power sources to power the gyro flight instruments and de-ice systems.

1H5 Series (all dash numbers)                         — Check Valve Manifolds (Vacuum System)
1H24 Series (all dash numbers) and 2H24-8   — Check Valve Manifolds (Pressure System)
1H37 Series (all dash numbers)                       — Check Valves (Vacuum/Pressure System)
2H3-39 and 2H3-47                                          — Regulator Check Valve Manifolds (Vacuum                                                                               System)

The date of manufacture is encoded on the nameplate of these components. The numbers (1 through 12) indicate the month (January through December) of manufacture. The following letter combinations indicate the year of manufacture:

T = 1972         E = 1979          AB = 1986        AJ = 1993      AT = 2000       BC = 2007
V = 1973         F = 1980          AC = 1987        AK = 1994     AU = 2001       BD = 2008
W= 1974         H = 1981         AD =1988         AL = 1995      AV = 2002       BE = 2009
A = 1975         J = 1982          AE = 1989        AM= 1996      AW= 2003       BF = 2010
B = 1976         K = 1983         AF = 1990        AN = 1997      AY = 2004       BG = 2011
C = 1977         M = 1984        AG = 1991        AP = 1998      BA = 2005       BH = 2012
D = 1978         AA = 1985      AH = 1992        AR = 1999      BB = 2006       BJ = 2013

Mandatory Inspection Intervals*
Beginning five (5) years from date of manufacture, the serviceability of these components must be verified every twelve (12) months in accordance with the procedure provided in the mandatory testing instructions in this document.

Mandatory Replacement Times*
These pneumatic system check valve manifolds, check valves and regulator check valve manifolds must be replaced ten (10) years from date of manufacture.

Lycoming Service Instruction No. 1009AW - Recommended Time Between Overhaul Periods

MODELS AFFECTED:  All Lycoming Piston Aircraft Engines

NOTE

Incomplete review of al the information in this document can cause errors. Read the entire Service Instruction to make sure you have a complete understanding of the requirements.

This Service Instruction identifies the  established Time Between Overhaul (TBO) for Lycoming piston aircraft engines that have genuine Lycoming  parts only. The TBOs, herein, do not apply to Lycoming engine models that contain parts other than those supplied by Lycoming Engines.

The information in  this revision  of Service  Instruction  1009  is approved  as an Alternative  Means of Compliance (AMOC) for compliance with AD-2012-19­-01 paragraphs (f)(1)(i) and (f)(2)(i).

The TBOs take into account service  experience,  variations in operating conditions, and frequency of operation. However, because of variations  in  the manner in  which engines are operated  and maintained, Lycoming Engines cannot give  assurance that any individual operator will achieve the TBOs identified herein.

Continuous service assumes that the aircraft wil not be out of service for more than 30 consecutive days. If the aircraft is to be out of service for more than 30 consecutive days, refer to the latest revision of Service Letter L180.

Engine  deterioration in  the form of corrosion  (rust) and the  drying  out and hardening  of composition materials such as gaskets, seals, flexible hoses and fuel pump diaphragms can occur if an engine is out of service for an extended period of time. Due to the loss of a protective oil film after an extended period of inactivity, abnormal wear on soft metal bearing surfaces can occur during engine start. Therefore,  al engines that do  not accumulate  the  hourly  period  of TBO  specified  in  this publication are recommended to be overhauled in the twelfth year. 

Table 1 identifies the TBOs for Lycoming engine models used in fixed wing aircraft. Table 2 contains the TBOs for Lycoming engine models used on rotary wing aircraft.

Lycoming SI 1037P - Approved Pistons, Rings and Cylinders for Use on Lycoming Aircraft Engines

MODELS AFFECTED: All Lycoming opposed series aircraft engines .

TIME OF COMPLIANCE: When installing new rings, pistons, valves and cylinders.

This Service Instruction identifies part numbers for pistons, rings, cylinders and valve combinations currently available for use in Lycoming engines in Table 1.

CAUTION

CHROME-PLATED PISTON RINGS (IDENTIFIED BY THE LOWERCASE LETTER “c”

AFTER THE PART NUMBER) ARE USED IN PLAIN OR NITRIDED STEEL CYLINDER BARRELS, BUT NEVER IN CHROME-PLATED BARRELS. SERIOUS ENGINE DAMAGE WILL OCCUR IF CHROME-PLATED PISTON RINGS ARE INSTALLED IN CHROME PLATED CYLINDER BARRELS.

NOTE

Chrome plated cylinder assemblies and kits containing chrome plated cylinders are no longer available from Lycoming Engines. However, compatible piston and ring combinations used with chrome-plated cylinders are still available and identified herein.

NOTE

For replacement piston rings, there could be different piston ring combinations for cylinders

with different materials use for the barrel.

Engine models that have serial number suffix “A” or “E” are built with crankcase configurations for wide cylinder base mounting flanges, and consequently must be assembled with wide deck cylinders.

Table 1 uses alphabetical symbols to identify various components as follows:

C* - Chrome plated steel cylinder barrel

FW - Full-Wedge compression ring

HW - Half-Wedge compression ring

N - Nitride hardened steel cylinder barrel

P - Plain steel cylinder barrel

S - Suffix to piston P/N to indicate service application

a - 3/16 inch “wide” oil regulating ring

b - 5/32 inch “narrow” oil regulating ring

c - Chrome plated piston ring

d - Cold forged piston

e - Requires long reach spark plugs

f - 1/2 inch diameter Inconel sodium cooled exhaust valve

g - 1/2 inch diameter sodium cooled exhaust valve

h - 7/16 inch diameter sodium cooled exhaust valve

j - 1/2 inch diameter chrome plated sodium cooled stem exhaust valve

k - Solid stem exhaust valve

m - 1/2 inch diameter Nimonic sodium cooled exhaust valve (TIO/TIGO-541)

p - Plain steel ring

r - Angle valve cylinder head (cylinders not marked “r” have parallel valves)

* - If choked chrome cylinder assemblies are used in any of the engine applications in Table 1, the compression ring gap must be increased to 0.045/0.055 inch (1.143 to 1.397 mm) which is the same for nitrided cylinder assemblies. Refer to the latest revision of SSP-1776, Table of Limits.