Ercoupe 415-C AD list


Ercoupe AD List - Dated June, 2012

Airframe,Univair Aircraft Corporation, 415-C.

46-23-01 - Muffler replacement

ERCO: (Was Mandatory Note 4 of AD-718-6.) Applies Only to 415-C, -CD and -D Aircraft Serial Numbers 113 to 362, Inclusive.

To be accomplished within next 50 hours of operation.

Trouble in service has indicated the necessity for replacing the original muffler on the serial numbers listed above with a new muffler, Erco P/N 145-40517.

(Erco Service Department Memorandum No. 7 dated February 1, 1946, covers this same subject.)

46-23-02 - Engine breather line hose

ERCO: (Was Mandatory Note 5 of AD-718-6.) Applies Only to 415-C, -CD and -D Aircraft Serial Numbers 113 to 263, Inclusive.

The flexible hose in the engine breather line should be inspected immediately. If the inner liner of this hose is an amber color, it is susceptible to contraction and possible clogging. Hose which shows evidence of clogging should be replaced at once by hose supplied by Erco or by equivalent hose such as AN 884 or AN 878. If hose has an amber lining but is still in satisfactory condition, it may be continued in service for a maximum of 25 hours, whereupon it must be replaced by satisfactory hose as described above.

(Erco Service Department Memorandum No. 11 dated February 1, 1946, covers this same subject.)

46-23-03 - Aileron control column fitting

ERCO: (Was Mandatory Note 3 of AD-718-6.) Applies Only to 415-C, -CD and -D Aircraft Serial Numbers 113 to 1306, Inclusive. To be accomplished immediately.

Due to the possibility of a defective fitting on the upper end of the control column shaft (Erco P/N 415-52129) in the aileron control system, the system should be tested to a load of 94 pounds, applied at the periphery of the control wheel. The ailerons should be blocked for the test. Each control wheel should be tested. The neutral position of the wheel should be noted before the test and if undue slack exists in the system it should be tightened. After the test, again note the neutral position and, if the position has changed more than about 5 degrees, the control column (part number above) should be replaced. If, after the test, the neutral position is within about 5 degrees of the original position, the ailerons should be freed and the system operated with the nose wheel on and off the ground. If the system operated freely and a visual inspection indicates that the system is in good condition, no change is necessary. An appropriate logbook entry shall be made to indicate that the above has been complied with. (Erco Service Bulletin No. 7 covers this same subject.)

46-38-02 - Aileron control stop

ERCO: (Was Mandatory Note 8 of AD-718-6.) Applies to 415-C, -CD and -D Aircraft Serial Numbers 113 to 2706 Except 2683, 2685, 2687, and 2691.

Compliance required prior to November 1, 1946.

(a) To provide additional bearing area and more positive locking action for the aileron control stop adjustment screw, add an AN 315-3R nut on the adjustment screw at the forward side of the stops and a star type AN 936-B10 lock washer (external teeth) between the jam nut and rear side of stops (Ercoupe P/N 415-52145).

(b) Inspect the welds which attach the aileron control stops to the control column cross member carefully for cracks. Also determine that welds are complete around the ends of the stops. Repair if cracked welds or insufficient welds are found.

(c) Inspect the adjustment of the two upper turnbuckles in the chain and cable system to be certain these turnbuckles do not touch the sprockets before the quadrant touches the stops. Readjust all three turnbuckles if necessary to insure freedom from this turnbuckle-sprocket interference.

(Erco Service Department Bulletin No. 13 covers this same subject.)

46-46-01 - Fuselage gas tank overflow line

ERCO: (Was Mandatory Note 9 of AD-718-6.) Applies Only to 415-C, -CD and -D Aircraft Serial Numbers 2623 to 2994, Inclusive.

Compliance required prior to January 1, 1947.

Install a new fuselage gas tank overflow line (Erco P/N 415-48162) and replace the imperial brass compression sleeve No. 60F with a rubber washer No. A549, Kohler Co. of A-64-3, Hayes Industries, Inc.

(Erco Service Department Bulletin No. 15, dated August 24, 1946, covers this same subject.)

46-49-01 - Nose wheel replacement

ERCO: (Was Mandatory Note 10 of AD-718-6.) Applies to All 415 Series Airplanes Equipped With Magnesium Die Cast Nose Wheel, Casting No. 34206. Compliance required prior to February 1, 1947. Due to an increasing number of failures of the Magnesium Die Cast Nose Wheel (which bears the number 34206 in raised letters), it appears essential that this wheel be replaced by a Permanent Mold Aluminum Alloy Nose Wheel (casting No. 34204) which the manufacturer is making available to all distributors and dealers. The replacement wheel, tire, and tube should be statically and dynamically balanced before use. Care should be exercised in removing the old nose wheel to avoid damaging the axle, oleo, and supporting structure. (Ercoupe Service Department Bulletin No. 16 dated October 28, 1946, covers this same subject in greater detail.)

47-20-03 - Fuel pump line alternation <Recurring>

ERCO: (Was Mandatory Note 11 of AD-718-6.) Applies to All 415 Series Aircraft Ercoupes Up to and Including Serial Number 3642 Which Incorporate Fuel Pumps With a Metal Filter Bowl, and Bearing AC P/N 1539076 on the Pump Mounting Flange. Inspection to be accomplished immediately, alteration to be made not later than the next periodic inspection. Inspect immediately and at each 25 hours thereafter until the following alteration is completed, the fuel pump lines near the pump for failure and leakage due to chafing. Alter fuel pump lines not later than next periodic inspection as follows: Remove the fuel pump top and rotate it 120 degrees clockwise (two screwholes from the original position). Replace the pump inlet port fittings with AN 842-4D elbow and the outlet port fittings with (415-48101-40) elbow having 1/16-inch restriction. Drill two 3/4-inch diameter holes in right front engine cooling baffle and install grommets (AN 931-9-13). Route fuel pump hoses through respective holes; shorten outlet hose (415-48101-2) and install fuel pump hose (415-48101-2 and 415-48101-3) onto respective elbows securing them with two hose clamps (AN 746-4). Safety-wire clamps. Close extra unused hole in baffle with button plug (415-40589-1) or equivalent. (Erco Service Department Memorandum No. 42 dated January 9, 1947, covers this same subject.)

47-20-04 - Baggage compartment zipper

ERCO: (Was Mandatory Note 12 of AD-718-6.) Applies to 415-C, -CD and -D Aircraft Serial Numbers 113 Through 4399.

To be accomplished prior to August 1, 1947.

A positive locking device must be installed on the zipper in the baggage compartment bottom to prevent its opening and permitting articles to fall through and foul the controls.

(Erco's Ercoupe Service Department Bulletin No. 17 dated January 6, 1947, covering this same subject, provides a satisfactory method for safetying the bottom baggage compartment zipper.)

47-20-05 - Belly skin reinforcement

ERCO: (Was Mandatory Note 13 of AD-718-6.) Applies to 415-C, -CD and -D Aircraft Serial Numbers 800 Through 2037.

Compliance required prior to October 1, 1947.

Cracks have occurred in the belly skin at the rearmost rivet attaching the center section belly skin outer stiffeners (Erco P/N 415-13056 L/R) to the belly skin.

To prevent similar failures where cracks have not yet developed, install 0.064-inch 24ST alclad angles 1/2-inch wide with legs of 1 3/32 inches and 1/2 inch (Erco P/N 415-13068). Attach the 1 3/32-inch leg to the outboard side of the aft end of each belly skin outer stiffener with two AN 470AD3-4 rivets (3/32-inch diameter, universal head, A17ST, 1/4-inch long) and to the center section rear beam with one AN 470AD3-5 rivet. (AN 430 type round head rivets may be used.)

If cracks are found in the belly skin, drill relief holes at the ends of the cracks and install triangular shaped patch plates as follows in addition to the angle stiffeners described above. Prepare the patch plates of 0.032-inch 24ST alclad material of such a shape that it will pick up the last two rivets which attach the aft end of the belly skin outer stiffener to the belly skin and the three rivets attaching the rear beam to the belly skin which are in line with and to either side of the stiffener. Remove the above-mentioned existing rivets and attach the patch plates through these holes using AN 470AD3-3 and -4 rivets. Attach the patch plate to the belly skin with six additional AN 470AD3-3 rivets, three through each side of each plate.

(Erco's Ercoupe Service Department Bulletin No. 18 dated January 9, 1947, covers this same subject.)

47-20-06 - Aileron reinforcement - superceeded

Superceeded by AD 2012-08-06.

47-20-06 ERCO: (Was Mandatory Note 14 of AD-718-6.) Applies Only to 415-C, -CD and -D Aircraft Serial Numbers 113-3784, Inclusive, Except the Following Which Have New Design Incorporated: 3719, 3720, 3723, 3724, 3726, 3729, 3732, 3735, 3738, 3741, 3742, 3744, 3745, 3747, 3750, 3753, 3756, 3759, 3762, 3764, 3765, 3767, 3768, 3771, 3774, 3777, 3780, 3783.

Compliance required not later than next 100-hour inspection unless visual inspection indicated immediate repair is required. Flexing of the lower aileron skin has resulted in fatigue cracks in the beam in the balance weight area. Inspect the beam and lower aileron skin carefully for cracks and drill relief holes at the ends of all cracks. Then add reinforcement plates (Erco P/N 415-16039-5 and -6) to the front face of the aileron beam and lower surface of the lower aileron skin, respectively, following the procedure outlined in Ercoupe Service Department Bulletin No. 20. (Blind, Type A, AN 450-4-10 may be used in lieu of Dupont Explosive DR134A-8 and DR134A-10 rivets, respectively.) Use new longer AN 526C632-7 truss head screws to reinstall the balance weight. Check the aileron rigging and the aileron bellcrank pushrod for freedom from binding in the rod end under full aileron travel before again placing the airplane in operation.

(Ercoupe Service Department Bulletin No. 20 dated February 17, 1947, covers this subject in greater detail.)

52-02-02 ERCO: Applies to All Model 415 Series and Models E and G Aircraft.

Compliance required as indicated.

As a result of several Ercoupe accidents, the following precautionary measures should be taken:

1. Before the next flight and at each 25-hour inspection:

(a) Inspect the aileron balance assembly (Erco P/N 415-16009) and ailerons for cracks in support structure and skin, respectively. Repair or replace defective parts.

(b) Inspect the four No. 6-32 screws which attach the balance weight support to the aileron for looseness and damage. Replace defective screws with AN 526-632 screws, taking care not to overstress during tightening.

2. Before next flight and at each 100-hour inspection, thereafter, inspect the aileron hinges and aileron control system for excessive looseness or wear in hinge pins or bearings. If, with one aileron blocked in the neutral position, the total play of the other aileron, measured at the trailing edge, exceeds 7/16-inch, all the joints and bearing should be checked and those which are loose should be tightened or replaced.

3. If the aileron balance weights have been removed in accordance with Erco Service Bulletin No. 57, item 1 above and AD 47-20-06 do not apply. However, any previous cracks in the aileron skin or beam which occurred prior to removal of the aileron balance weights must be repaired or the parts replaced. The free play referred to in item 2 above must be reduced to 5/16-inch.

4. Before the next flight, determine that the air speed instrument is distinctly marked in accordance with the operating limitations.

(Engineering and Research Corp. Service Memorandum No. 56 covers this same subject.)

This supersedes AD 49-02-02; the new material is contained in item 3.

47-20-08 - Battery box drain

ERCO: (Was Mandatory Note 16 of AD-718-6.) Applies to 415-C, -CD and -D Aircraft. Compliance required prior to July 1, 1947. (a) Install a new battery box drain tube to extend at least 1/2 inch below the fuselage belly skin if this has not been already incorporated in the airplane. (b) Examine the fuselage structure and controls carefully for corrosion. If corrosion is found on the structure, the affected areas should be washed with an alkaline solution and followed by a thorough clear water rinse. Corroded controls should be replaced. (c) Examine the baggage compartment for deterioration. If damage is evident, wash the affected area with a diluted alkaline solution and rinse with clear water. Reinforce any damaged areas with 10 1/2-ounce single filled water-resistant canvas, double sewn with 16-4 glace finished thread. (d) Install decalcomania (Erco P/N 415-54062) on the top of the battery box cover. (Ercoupe Service Department Memorandum No. 44 dated February 17, 1947, and Ercoupe Service Department Bulletins No. 8 dated May 24, 1946, and No. 22, dated February 3, 1947, also cover the above subjects.)

47-20-09 - Voltage regulator check <Recurring>

ERCO: (Was Service Note 1 of AD-718-6.) Applies to 415-C, -CD and -D Aircraft. Compliance required at each 100-hour inspection and immediately after each electrical system malfunction. Check the operation of the voltage regulator by observing the ammeter reading after starting and until the battery becomes charged. A normal operation would indicate a charging rate up to 11-13 amperes for periods of time up to 20 minutes after starting. The charging rate should reduce to 2 amperes or less within 2 hours or operation. (Ercoupe Service Department Memorandum No. 23 covers this same subject.)

47-42-20 - Control column shaft

ERCO: (Was Mandatory Note 17 of AD-718-7.) Applies Only to 415-C, -CD and -D Aircraft Serial Numbers 1033 to 1327, Inclusive. Compliance required not later than next 100-hour inspection. One of the above airplanes may contain a control column shaft, P/N 415-52129, which is defective at its lower bearing fitting. In order to ascertain whether the fitting is defective withdraw the shaft from the control column so the surface of lower control shaft fitting, P/N 415-52126, which bears on the lower bakelite bushing, can be examined. If a steel sleeve is found brazed to this lower shaft fitting's bearing surface, the shaft should be replaced and the defective shaft returned to the manufacturer. (Ercoupe Service Policy Letter No. B-10, covering the subject will be issued to each Ercoupe distributor.)

50-07-01 - Elevator trim tab stop

50-07-01 ERCO: Applies to Ercoupe Models 415C (Which Incorporate Adjustable Elevator Trim Tabs), 415CD, and 415D Airplanes. To be accomplished by September 1, 1950. To preclude the possibility of elevator flutter in the event the elevator trim tab control wire fails, elevator trim tab stop and spring, Erco P/N 415-SK-287 and 415-22035 should be installed. (Engineering and Research Corp. "Ercoupe Service Memorandum No. 55 and 55A" cover this same subject.)

52-02-02 - Aileron inspection <Superceeded>

Superceeded by AD 2012-08-06.

Compliance required as indicated.

As a result of several Ercoupe accidents, the following precautionary measures should be taken:

1. Before the next flight and at each 25-hour inspection:

(a) Inspect the aileron balance assembly (Erco P/N 415-16009) and ailerons for cracks in support structure and skin, respectively. Repair or replace defective parts.

(b) Inspect the four No. 6-32 screws which attach the balance weight support to the aileron for looseness and damage. Replace defective screws with AN 526-632 screws, taking care not to overstress during tightening.

2. Before next flight and at each 100-hour inspection, thereafter, inspect the aileron hinges and aileron control system for excessive looseness or wear in hinge pins or bearings. If, with one aileron blocked in the neutral position, the total play of the other aileron, measured at the trailing edge, exceeds 7/16-inch, all the joints and bearing should be checked and those which are loose should be tightened or replaced.

3. If the aileron balance weights have been removed in accordance with Erco Service Bulletin No. 57, item 1 above and AD 47-20-06 do not apply. However, any previous cracks in the aileron skin or beam which occurred prior to removal of the aileron balance weights must be repaired or the parts replaced. The free play referred to in item 2 above must be reduced to 5/16-inch.

4. Before the next flight, determine that the air speed instrument is distinctly marked in accordance with the operating limitations.

(Engineering and Research Corp. Service Memorandum No. 56 covers this same subject.)

This supersedes AD 49-02-02; the new material is contained in item 3.

52-25-02 - Federal nose ski

ERCOUPE: Applies to Models 415-C and -CD Aircraft Having a 5.00x4 Nose Wheel and Using Federal Skis.

To be accomplished not later than December 1, 1952.

To eliminate instances of the nose ski coming off when operating on Federal Aircraft Works Model A-1500 skis, a supplementary safety device should be installed. A simple and suitable device is a rectangular plate (approximately 1/8-inch thick and 1/2-inch longer than axle diameter) installed to end of axle stub so that ends of plate will prevent retaining nut from backing off if lock washer fails. This plate, which will also provide for visual inspection of retaining nut, to be held in place by a safetied through bolt. This modification can easily be made and installed in the field. Drawing (No. ES-B-203) describing such an installation is available from Federal Aircraft Works, Minneapolis, Minn.

(Federal Service Bulletin No. 100 also covers this subject.)

54-26-02 - Control cable fraying<Recurring>

Applies to All Ercoupe Model 415 Series Aircraft and Models E and G.

Compliance required as indicated.

As a result of continual fraying and failure of control cables P/N 415-52148 or P/N 415-52172 in the control column assembly where they wrap around the control quadrant P/N 415-52130 or P/N 415-52122 the following inspection must be conducted until such time as a control quadrant is installed which is considered satisfactory by the Administrator:

After every 100 hours of operation remove control cables P/N 415-52148 or P/N 415-52172 and inspect them for any signs or indications of fraying or failure. Replace any cables which are not found to be in perfect condition. It is important that the cables be removed for the inspection since it has been found that inspection of the cables while in place will not always reveal defects. Also determine whether the aileron stop screw may be bearing on the cable, and, if so, it should be replaced by new stop bolt Erco P/N 415-52164-2.

Modifications approved by the FAA which are believed to eliminate the fraying difficulties are described in the following data:

1. Drawing No. 514, change "A", Met-Co-Aire Co., Fullerton Municipal Airport, Fullerton, Calif.;

22. Drawing No. New 101, change "A," J.V. Newman, Bates Aviation Inc., Hawthorne Municipal Airport, Hawthorne, Calif.

3. Drawing No. 12, dated November 1, 1954, Ed's Airmotive, 430 Windsor Way, Renton 2, Wash.;

4. Drawing No. 415-52137, change "1," dated February 21, 1955, Vest Aircraft Parts Division, Denver, Colo.

When one of these or an equivalent FAA-approved modification has been installed, the special 100-hour inspection outlined above may be dispensed with and normal inspection period resumed.

Rigging of controls should follow the process outlined in Ercoupe Service Department Bulletin No. 13 and Ercoupe Service Department Memorandum No. 35.

This supersedes AD 47-42-21.

55-22-02 - Terneplate fuel tank<Recurring>

ERCO: Applies to 415-C, -CD and -D Aircraft Serial Numbers 113 Through 2468 for Fuselage Tank Replacement; Serial Numbers 113 Through 2622 For Wing Tank Replacements.

Inspection required each 25 hours; replacement at time leakage discovered.

Unless the terneplate fuselage fuel tank has been replaced with a stainless steel tank and the terneplate wing fuel tanks replaced with aluminum alloy or stainless steel tanks, the tanks should be inspected frequently for signs of leakage at intervals not greater than 25 hours. If tank leakage is observed, the tank should be replaced with one of stainless steel or aluminum alloy, as required, before the next flight.

Erco Service Department Bulletins No. 10 and No. 10A and Memorandums No. 31 and 43 pertain to the inspection and replacement of these tanks.

This supersedes AD 47-50-10.

57-02-01 - Rudder horn attachment <Recurring>

FORNEY (ERCOUPE): Applies to All Models 415-C, -CD, -D, E, G and F-1 Aircraft. Compliance required at every 100 hours. There have been several failures of the rudder horn attachments. Experience has indicated that these failures are attributed to improper ground handling technique rather than to unusual flight loads. The design of the aircraft has placed the fins and rudders at the height which owners and operators have found convenient for pushing or pulling with their hands when moving the airplane in and out of hangers and along the ground. Such handling tactics will subject the surfaces to higher loads than those for which they are designed and should be avoided. The following inspection would be made and corrective action taken when necessary.

A load of 10 pounds should be applied to the trailing edge of the rudder while the controls are locked in neutral position. The trailing edge should not deflect more than one-half inch, nor should there be evidence of a clicking noise occurring in the vicinity of the center rudder hinge when the rudder is deflected. If the deflection exceeds 1/2 inch, the control system should be checked to establish that the deflection is in the rudder. Once the deflection has been established as in the rudder or if a clicking noise is heard even though the deflection was less than 1/2 inch, the rudder should be removed and the main spar inspected for cracks. The outboard skin should also be removed sufficiently to inspect the rudder horn attaching structure and the roots of the rudder ribs for cracks or damage. Any parts found cracked or deformed should be replaced. (Except for the cracked rudder ribs, Ercoupe Service Bulletin No. 25, dated July 31, 1953, covers this same subject.) This supersedes AD 53-26-02.

59-05-04 - Rear spar reinforcement <Recurring>

ERCOUPE: Applies to All Models 415-C, 415-CD, 415-D, E and G. Compliance to be accomplished within the next 100 hours of operation. Frequent failures of the rear spar center section have been found on Ercoupe Model aircraft. These failures follow the same pattern in that the rear spar P/N 415-13048 L/R failed due to cracking of the upper flange in the area of the intersection of the rear spar with the fuselage side on either the right or left spar assembly. Repairs made in the field with gusset plates have been found to be only partially satisfactory and in most instances did not keep the crack from progressing into the spar web. This damage to the spar has been attributed to the following: (1) Rough landings coupled with a lack of fluid in the oleo struts. (2) Taxiing at high speeds over rough terrain. (3) A combination of (1) and (2) with the structure weakened by corrosion due to no protective coating of the spar. In view of the above, it is mandatory that the rear spar on Forney (Ercoupe) aircraft be inspected and action taken as follows: (1) If no damage or cracks are found, the spar must be reinforced by stiffener angle P/N F-13109 or equivalent. The spar may be considered satisfactory if previously reinforced with P/N 415-13108 or equivalent. (2) If damage or crack exists but does not extend into the spar web, a repair may be made by the addition of stiffener P/N F-13109 or equivalent provided an inspection every 100 hours of service life thereafter discloses no further progressive damage. If damage is found to progress, then a new spar and stiffener must be installed. If damage or crack extends into the spar web, the spar must be replaced. (3) If a new spar and stiffener is installed, the 100-hour inspection requirement in (2) above may be eliminated. (Forney Manufacturing Company, Aviation Division, Fort Collins, Colorado, Service Memorandum 53A supersedes Service Memorandum 53 and covers this same subject.) This supersedes AD 57-13-03.

59-25-05 - Rudder reinforcement <Recurring>

FORNEY (ERCOUPE): Applies to All (Ercoupe) Forney Aircraft With Serial Numbers Up to 3,335 Inclusive. Compliance required by December 31, 1959, and thereafter every 100 hours of operation or periodic inspection, whichever occurs first. Fatigue failures have continued to occur in the rudder main rib where the control horn is attached after installation of reinforcement plates. Therefore, it is required that a visual inspection be made of the area around the rudder control horn for excessive deflection of the horn, canning of rudder skin, or any other unusual peculiarity which would indicate main rudder rib damage. If damage is evident, rudder rib Erco P/N 415-240 12 L/R must be replaced with Forney P/N F-24015 L/R or equivalent. This inspection may be discontinued when the heavier gage rib is installed. (Forney Service Bulletin No. 105 covers this subject.) This supersedes AD 47-20-07.

60-09-02 - Nose gear bolts

FORNEY: Amdt. 137 Part 507 Federal Register April 30, 1960. Applies to Models Erco 415 Series and Aircoupe F-1 Aircraft Serial Numbers 1 Through 5678 Incorporating Electrol Hose Gear With Aluminum Scissors.

Compliance required not later than July 1, 1960.

Bolts used to attach the forged aluminum scissors to the electrol nose gear were found to be brittle. To preclude failure of these bolts and the danger of the nose wheel turning crosswise during landing, the following shall be accomplished:

Replace bolts, P/N 415-34330, with AN 5-26 bolts, AN 960 washers (two per bolt) and AN 310-5 nuts. The tightened nut must not cause binding.

(Forney Service Bulletin No. 103 covers this same subject.)

67-06-03 - Rudder bellcrank

ERCOUPE: Amdt. 39-349 Part 39 Federal Register February 11, 1967. Applies to Models 415C, 415CD, 415D, E, G, and F1 Series Airplanes, Serial Numbers 1 through 5714 inclusive, Except Those Airplanes Modified in Accordance with Either Ercoupe Service Memorandum No. 63 or Air Products Document No. 110.

Compliance required as indicated.

To prevent loss of rudder control, accomplish the following:

(a) Before further flight, after the effective date of this AD, with the nosegear raised off the ground, inspect the rudder control system by checking the rudder controls from the cockpit for freedom of movement through the entire range of rudder control travel. If any restriction or impediment on the normal freedom of movement of the rudder controls is apparent, the cause thereof must be determined prior to further flight. If it is determined that the restriction or impediment is caused by binding in the rudder bellcrank at the stabilizer, before further flight, modify the rudder bellcrank assembly in a manner prescribed in (c) of this AD.

(b) If the rudder bellcrank assembly is not modified as a result of findings made during the inspection provided in (a), then it must be modified in a manner prescribed in (c) of this AD within fifty (50) hours time in service after the effective date of this AD.

(c) Modify the rudder bellcrank assembly in accordance with any one of the following -

(1) One of the two methods contained in Alon Service Bulletin No. 14, dated February 3, 1967; or

(2) The method contained in Ercoupe Service Memorandum No. 63 (available upon request from Alon, Inc., Municipal Airport, McPherson, Kansas); or,

(3) Any other method approved as equivalent by the Chief, Engineering and Manufacturing Branch, Federal Aviation Agency, Central Region.

This directive effective February 11, 1967.

2002-16-04 - Prevent failure of the fuel line fittings or the gascolator

SUMMARY: This amendment supersedes two different airworthiness directives that require you to inspect the fuel line nipple for damage, replace any suspect part, and replace the elbow fitting on certain Univair Aircraft Corporation (Univair) Models (ERCO) 415-C, (ERCO) 415-CD, (ERCO) 415-D, (ERCO) 415-E, (ERCO) 415-G, (Forney) F-1, and (Forney) F-1A airplanes.

This AD requires you to accomplish the following on airplanes with the gascolator connected to the side of the carburetor:

Replace any aluminum fuel line nipple or elbow fitting with a brass or steel fuel line nipple or elbow fitting, inspect for double support tubes on the gascolator, install these tubes if they do not exist, and inspect the fuel line fittings between the carburetor and gascolator for cracks or misalignment and replace as necessary.

This AD will not affect those airplanes with the gascolator mounted on the firewall. This AD is a result of cracks in the subject area on airplanes in compliance with the current ADs.

The actions specified by this AD are intended to prevent failure of the fuel line fittings or the gascolator because of the current airplane design configuration (aluminum fuel line nipples, aluminum fuel line elbows, and/or no double support tubes on the gascolator). Such failure could result in a lack of fuel to the engine with consequent loss of control of the airplane.

See also the Univair instructions as PDF file

2002-26-02 - Detect and correct corrosion in the wing center section <Recurring>

2002-26-02 Univair Aircraft Corporation: Amendment 39-12987; Docket No. 2001-CE-45-AD.

(a) What airplanes are affected by this AD? This AD affects the following airplane models and serial numbers that are certificated in any category:

Models : ERCO 415-C, 415-CD, 415-D, 415-E, and 415-G.; Forney F-1 and F-1A ; Alon A-2 and A2-A ; Mooney M10 Serial Numbers: All.

(b) Who must comply with this AD? Anyone who wishes to operate any of the airplanes identified in paragraph (a) of this AD must comply with this AD.

(c) What problem does this AD address? The actions specified by this AD are intended to detect and correct corrosion in the wing center section which could result in failure of the wing center section structure during flight. Such failure could lead to loss of control of the airplane.

(d) What actions must I accomplish to address this problem? To address this problem, you must accomplish the following:

ActionsComplianceProcedures
(1) Inspect the wing center section
for corrosion or corrosion damage by
accomplishing one of the following:
(i) Install inspection openings to gain
access to the wing walkway box structure
and inspect the wing center structure
for corrosion or corrosion damage;
(ii) Use a scope and light source, e.g., fiberscope borescope or an endoscope (as specified in paragraph (e) of this AD) to inspect the wing center structure for corrosion or corrosion damage); or
(iii) Remove the outer wing panels to gain visual access to the wing walkway box structure for corrosion or corrosion damage.
Within the next 12 calendar months after February 14, 2003 (the effective date of this AD) and thereafter at intervals not to exceed 3 years.In accordance with the Procedures section of Univair Aircraft Corporation Service Bulletin No. 31, dated January 29, 2002; or Univair Aircraft Corporation Service Bulletin No. 31, Revision 1, dated June 14, 2002; and Advisory Circular 43-4A, Corrosion Control for Aircraft.
(2) If corrosion or corrosion damage is found during any inspection required in paragraph (d)(1) of this AD, repair or replace damaged components of the wing center section.Prior to further flight after any inspection in which the corrosion or corrosion damage is found.In accordance with the Procedures section of Univair Aircraft Corporation Service Bulletin No. 31, dated January 29, 2002; or Univair Aircraft Corporation Service Bulletin No. 31, Revision 1, dated June 14, 2002; the applicable maintenance manual; and Advisory Circular 43-4A, Corrosion Control for Aircraft.
(3) If inspection openings are installed in accordance with paragraph (d)(1)(i) of this AD, install cover plate assemblies.Prior to further flight after each inspection or repair required in paragraphs (d)(1) and (d)(2) of this AD.In accordance with the Procedures section of Univair Aircraft Corporation Service Bulletin No. 31, dated January 29, 2002; or Univair Aircraft Corporation Service Bulletin No. 31, Revision 1, dated June 14, 2002.
(4) If any damage is found during any inspection required by this AD, submit a Malfunction or Defect Report (M or D), FAA Form 8010-4, to the FAA.
(i) Include the airplane model and serial number, the extent of the damage (location and type), and the total number of hours TIS on the damaged area.
(ii) You may submit M or D reports electronically by accessing the FAA AFS-600 Web page at http://av-info.faa.gov/isdr. You will lose access to the report once electronically submitted. We recommend you print two copies prior to submitting the report. Forward one copy to the Denver Aircraft Certification Office (ACO) and keep the one copy for your records. The Office of Management and Budget (OMB) approved the information collection requirements contained in this regulation under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and assigned OMB Control Nubmer 2120-0056.
Within 10 days after the inspection in which the corrosion or damage was found or within 10 days after February 14, 2003 (the effective date of this AD), whichever occurs later.Send the report to Roger Caldwell, FAA, at the address in paragraph (g) of this AD. You may also file electronically as discussed in this AD.

e) What kind of scope or light source must I use to accomplish the inspection required in paragraph (d)(1)(ii) of this AD? We have determined that Olympus OSF Endoscope (sigmoidoscope) with a Fujinon FIL-150 light source is acceptable for the inspections option chosen in paragraph (d)(1)(ii) of this AD. Other scopes and light sources are acceptable and must meet the following minimum characteristics: (1) Must be a remote high intensity light source of 150 Watts halogen or better.

(2) The optical system must be of a quality such that it remains constantly in focus from about 4 millimeters (0.16 inch) to infinity.

(3) When the tip is approximately 4 millimeters from the inspected surface, a magnification of about 10X must be achieved.

(4) The image guide and protective sheath length must be at least 2 feet for more, and the distal tip diameter must be 0.450 inch or larger.

(5) There must be control handles for four-way tip articulation of the last 4 to 5 inches for a minimum of 100 degrees for each direction.

(f) Can I comply with this AD in any other way? You may use an alternative method of compliance or adjust the compliance time if:

(1) Your alternative method of compliance provides an equivalent level of safety; and

(2) The Manager, Denver Aircraft Certification Office (ACO), approves your alternative. Submit your request through an FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Denver ACO.

Note: This AD applies to each airplane identified in paragraph (a) of this AD, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (f) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if you have not eliminated the unsafe condition, specific actions you propose to address it.

(g) Where can I get information about any already-approved alternative methods of compliance? Contact Roger Caldwell, Aerospace Engineer, FAA, Denver Aircraft Certification Office, 26805 East 68th Avenue, Room 214, Denver, Colorado 80249-6361; telephone: (303) 342-1086; facsimile: (303) 342-1088.

(h) What if I need to fly the airplane to another location to comply with this AD? The FAA can issue a special flight permit under sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate your airplane to a location where you can accomplish the requirements of this AD.

(i) Are any service bulletins incorporated into this AD by reference? Actions required by this AD must be done in accordance with Univair Aircraft Corporation Service Bulletin No. 31, dated January 29, 2002; or Univair Aircraft Corporation Service Bulletin No. 31, Revision 1, dated June 14, 2002. The Director of the Federal Register approved this incorporation by reference under 5 U.S.C. 552(a) and 1 CFR part 51. You may get copies from Univair Aircraft Corporation, 2500 Himalaya Road, Aurora, Colorado 80011. You may view copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

(j) When does this amendment become effective? This amendment becomes effective on February 14, 2003.

See drawing of inspection holes.
2003-21-01 - Prevent wing damage caused by a corroded wing outer panel structural component <Recurring>

003-21-01 Univair Aircraft Corporation: Amendment 39-13335; Docket No. 2002-CE-58-AD; Supersedes AD 94-18-04 R1, Amendment 39-9173.

When Does This AD Become Effective?

(a) This AD becomes effective on December 1, 2003.

What Other ADs Are Affected by This Action?

(b) This AD supersedes AD 94-18-04 R1, Amendment 39-9173.

What Airplanes Are Affected by This AD?

(c) This AD affects the following airplane models and serial numbers that are certificated in any category: Alon A-2 and A2-A - ALL ERCO 415-C, 415-CD, 415-D, 415-E, and 415-G. - ALL Forney F-1 and F-1A. - ALL Mooney M10 - ALL

What Is the Unsafe Condition Presented in This AD?

(d) This AD is the result of additional reports of corrosion on airplanes in compliance with AD 94-18-04 R1. The actions specified in this AD are intended to prevent wing damage caused by a corroded wing outer panel structural component, which, if not detected and corrected, could progress to the point of structural failure.

What Must I Do To Address This Problem?

(e) To address this problem, you must accomplish the following:

ActionsComplianceProcedures
(1) Install inspection openings in the outer wing panels and inspect the wing outer panel internal structural components for corrosion and unrepaired corrosion damageWithin the next 12 calendar months after March 24, 1995 (the effective date of AD 94-18-04 R1), unless already accomplished.In accordance with Univair Service Bulletin No. 29, Revision B, dated January 2, 1995, or Univair Service Bulletin No. 29, Revision C, dated July 8, 1999, and Advisory Circular 43-4A, Corrosion Control for Aircraft.
(2) If corrosion or corrosion damage is found during the inspection required in paragraph (e)(1) of this AD, repair or replace components of the wing outer panel structure.Repair or replace prior to further flight after the inspection required in paragraph (e)(1) of this AD.In accordance with Univair Service Bulletin No. 29, Revision B, dated January 2, 1995, or Univair Service Bulletin No. 29, Revision C, dated July 8, 1999, the applicable maintenance manual, and Advisory Circular 43-4A, Corrosion Control for Aircraft.
(3) Repetitively inspect the wing outer panel internal structural components for corrosion and unrepaired corrosion damage.Initially inspect within the next 6 calendar months after December 1, 2003 (the effective date of this AD), unless the wing outer panel internal structure has been inspected for corrosion within the previous 6 calendar months immediately prior to December 1, 2003 (the effective date of this AD). Repetitively inspect thereafter at intervals not to exceed 12 calendar months after the last inspection.In accordance with Univair Service Bulletin No. 29, Revision C, dated July 8, 1999, and Advisory Circular 43-4A, Corrosion Control for Aircraft.
(4) At any time corrosion or corrosion damage is found, repair or replace components of the wing outer panel structure.Repair or replace prior to further flight after the inspection in which the corrosion or corrosion damage is found. Continue with the repetitive inspection requirements of this AD.2In accordance with Univair Service Bulletin No. 29, Revision B, dated January 2, 1995, or Univair Service Bulletin No. 29, Revision C, dated July 8, 1999, and Advisory Circular 43-4A, Corrosion Control for Aircraft.

Note: The compliance times specified in Univair Aircraft Corporation Service Bulletin No. 29, Revision B, dated January 2, 1995, or Univair Service Bulletin No. 29, Revision C, dated July 8, 1999, are different from those required by this AD. The compliance times in this AD take precedence over those in the service bulletin.

What About Alternative Methods of Compliance?

(f) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.13.

(1) Send your request to the Manager, Denver Aircraft Certification Office (ACO). For information on any already approved alternative methods of compliance, contact Roger Caldwell, Aerospace Engineer, FAA, Denver Aircraft Certification Office, 26805 East 68th Avenue, Room 214, Denver, Colorado 80249-6361; telephone: (303) 342- 1086; facsimile: (303) 342-1088.

(2) Alternative methods of compliance approved for the inspection required in AD 94-18-04 R1, which is superseded by this AD, are approved as alternative methods of compliance with this AD.

Is There Material Incorporated by Reference?

(g) You must do the actions required by this AD per Univair Aircraft Corporation Service Bulletin No. 29, Revision B, dated January 2, 1995, and Univair Service Bulletin No. 29, Revision C, dated July 8, 1999.

(1) The Director of the Federal Register approved the incorporation by reference of Univair Aircraft Corporation Mandatory Service Bulletin No. 29, Revision C, dated July 8, 1999, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You may get a copy from Univair Aircraft Corporation, 2500 Himalaya Road, Aurora, Colorado 80011, telephone: (303) 375-8882; facsimile: (303) 375- 8888.

(2) The Director of the Federal Register previously approved the incorporation by reference of Univair Aircraft Corporation Service Bulletin No. 29, Revision B, dated January 2, 1995, as of March 24, 1995 (60 FR 13626, March 14, 1995).

(3) You may review copies at FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

The PDF copy for a detailed explanation

AD 2012-08-06 - inspections of the ailerons, aileron balance assembly, and aileron rigging <Recurring>

SUMMARY: We are superseding an existing airworthiness directive (AD) for certain Univair Aircraft Corporation Models (ERCO) 415-C, 415-CD, 415-D, E, G; (Forney) F-1 and F-1A; (Alon) A-2 and A2-A; and (Mooney) M10 airplanes. That AD currently requires an inspection of the aileron balance assembly and ailerons for cracks and excessive looseness of associated parts with the required repair or replacement of defective parts as necessary. This new AD would add airplanes to the Applicability section; require inspections of the ailerons, aileron balance assembly, and aileron rigging for looseness or wear, require repair or replacement of parts as necessary; and require a report of the inspection results. This new AD was prompted by a report of a Univair Aircraft Corporation Model ERCO 415-D Ercoupe that crashed after an in-flight breakup due to possible aileron flutter. We are issuing this AD to correct the unsafe condition on these products.

Required Actions
What must be done?When must it be done?How it must be done
(1) For all airplanes: Inspect the ailerons for cracks in the support structure and skin.Within the next 25 hours time-in-service (TIS) after October 3, 2012 (the effective date of this AD) or within 3 months after October 3, 2012 (the effective date of this AD), whichever occurs first. Repetitively thereafter inspect at intervals not to exceed 100 hours TIS or 12 months, whichever occurs first.For all airplanes except the Mooney M10, follow Ercoupe Service Memorandums No. 56 and 35A, both Revisions A, both dated September 1, 2008. For the Mooney M10 follow the Mooney M10 Service and Maintenance Manual, Serial Numbers 690001 through 690011 and 700001 and on, Revision A, dated September 1, 2008, Section V, pages 51 through 54.
(2) For airplanes with the aileron balance assembly (ERCO Part Number (P/N) 41516009) installed: Inspect the assembly for cracks in the support structure and skin.Within the next 25 hours TIS after October 3, 2012 (the effective date of this AD) or within 3 months after October 3, 2012 (the effective date of this AD), whichever occurs first. Repetitively thereafter inspect at intervals not to exceed 100 hours TIS or 12 months, whichever occurs first.Follow Ercoupe Service Memorandums No. 20, 56, and 57, all Revisions A, all dated September 1, 2008; and for Models E and (Forney) F1 and F1A, follow Ercoupe Service Memorandum No. 35A, Revision A, dated September 1, 2008.
(3) For all airplanes: If any cracking is found during the inspections required in paragraphs (g)(1) and/or (g)(2) of this AD, repair or replace cracked parts.Before further flight after the inspection where the cracking was found.Follow Ercoupe Service Memorandums No. 20, 56, and 57, all Revisions A, all dated September 1, 2008; and for Models E and (Forney) F1 and F1A, follow Ercoupe Service Memorandum No. 35A, Revision A, dated September 1, 2008.
(4) For airplanes with the aileron balance assembly (ERCO P/N 41516009) installed: Inspect the four No. 632 screws that attach the balance weight support to the aileron for looseness and damage.Within the next 25 hours TIS after October 3, 2012 (the effective date of this AD) or within 3 months after October 3, 2012 (the effective date of this AD), whichever occurs first. Repetitively thereafter inspect at intervals not to exceed 100 hours TIS or 12 months, whichever occurs first.Follow Ercoupe Service Memorandums No. 20, 56, and 57, all Revisions A, all dated September 1, 2008; and for Models E and (Forney) F1 and F1A, follow Ercoupe Service Memorandum No. 35A, Revision A, dated September 1, 2008.
(5) For all airplanes: If any looseness or damage is found during the inspection of the screws required in paragraph (g)(4) of this AD, replace the screws with AN 526632 screws, making sure to not overstress during tightening.Before further flight after the inspection where the looseness or damage was found.Follow Ercoupe Service Memorandums No. 20, 56, and 57, all Revisions A, all dated September 1, 2008; and for Models E and (Forney) F1 and F1A, follow Ercoupe Service Memorandum No. 35A, Revision A, dated September 1, 2008.
(6) For airplanes with the aileron balance assembly (ERCO P/N 41516009) installed: Inspect the aileron hinges and aileron control system for excessive looseness or wear in hinge pins or bearings. If, with one aileron blocked in the neutral position, the total play of the other aileron, measured at the trailing edge, exceeds 7⁄16-inch, inspect all the joints and bearings and tighten or replace those which are loose.Within the next 25 hours TIS after October 3, 2012 (the effective date of this AD) or within 3 months after October 3, 2012 (the effective date of this AD), whichever occurs first. Repetitively thereafter inspect at intervals not to exceed 100 hours TIS or 12 months, whichever occurs first.Follow Ercoupe Service Memorandums No. 20, 56, and 57, all Revisions A, all dated September 1, 2008; and for Models E and (Forney) F1 and F1A, follow Ercoupe Service Memorandum No. 35A, Revision A, dated September 1, 2008.
(7) For airplanes that do not have the aileron balance assembly (ERCO P/N 41516009) installed: Inspect the aileron hinges and aileron control system for excessive looseness or wear in hinge pins or bearings. If, with one aileron blocked in the neutral position the total play of the other aileron, measured at the trailing edge, exceeds 5⁄16-inch, inspect all the joints and bearings and tighten those which are loose.Within the next 25 hours TIS after October 3, 2012 (the effective date of this AD) or within 3 months after October 3, 2012 (the effective date of this AD), whichever occurs first.Follow Ercoupe Service Memorandums No. 20, 56, and 57, all Revisions A, all dated September 1, 2008; and for Models E and (Forney) F1 and F1A, follow Ercoupe Service Memorandum No. 35A, Revision A, dated September 1, 2008.
(8) For all airplanes: Determine that the airspeed instrument is correctly calibrated and distinctly marked in accordance with the operating limitations.Within the next 25 hours TIS after October 3, 2012 (the effective date of this AD) or within 3 months after October 3, 2012 (the effective date of this AD), whichever occurs first, and repetitively thereafter every four years, and any time maintenance occurs that affects the system integrity.For airspeed instrument calibration by bench test method, you must use an FAA-authorized instrument repair facility. For airspeed calibration by global positioning system (GPS) or other owner/operator FAA-approved method, you may follow the instructions in Advisory Circular (AC) AC 238C, Appendix 9, dated November 16, 2011. AC 238C can be found at: www.airweb.faa.gov look for 23-8C.pdf.
(9) For all airplanes except the Mooney M10: Remove load from nose wheel and adjust rigging.Within the next 25 hours TIS after October 3, 2012 the effective date of this AD) or within 3 months after October 3, 2012 (the effective date of this AD), whichever occurs first. Repetitively thereafter adjust at intervals not to exceed 100 hours TIS or 12 months, whichever occurs first.Follow Ercoupe Service Memorandum No. 35, Revised January 6, 2006, and/or Ercoupe Service Memorandum 35A, Revision A, dated September 1, 2008.
(10) For all airplanes: Submit a one-time report from the initial inspections and/or actions required in paragraphs (g)(1), (g)(2), (g)(4), (g)(6), (g)(7), (g)(8), and (g)(9) of this AD.Within 30 days after the initial inspections and/or actions required in paragraphs (g)(1), (g)(2), (g)(4), (g)(6), (g)(7), (g)(8), and (g)(9) of this AD, or 30 days after October 3, 2012 (the effective date of this AD) if you are using the unless already done credit.Use the reporting form found in Figure 1 of paragraph (g)(10) of this AD and send the report to the following offices: Roger A. Caldwell, Aerospace Engineer, FAA, ANM100D, Denver Aircraft Certification Office (ACO), 26805 East 68th Avenue, Room 214, Denver, Colorado 802496361; and Univair Aircraft Corporation, 2500 Himalaya Road, Aurora, Colorado 80011.

AD 2012-08-06 Aileron / rudder control plus ASI check - recurring AD-2012-0806.pdf

Also the Advisory Circular Information AC 23-8C on flight tests and ASI calibration here for download. It is 8 MB in size. 23-8C.pdf



Engine,Teledyne Continental, C85-12F.

47-40-02 - Piston pins

47-40-02 CONTINENTAL: (Was Mandatory Note of Airworthiness Directive Supplement Dated October 3, 1947.) Applies Only to the Following Models: Cessna 120 and 140, Commonwealth (Rearwin) 185, Superior (Culver) V and V2, Air Products (Erco) 415C, McClish (Funk) B85C, Universal (Globe) GC-1A, GC-1B, Silvaire (Luscombe) 8E, and Piper J3C-65, J4E, J5A Having Continental C75-12 or -12F Engines With Serial Numbers Below 1794-6-12 Except 1788-6-12: Airplanes Having Continental C85-12, -12F or -12FHJ Engines With Serial Numbers Below 20668-6-12 Except: 20656-6-12, 20658-6-12, 20659-6-12, 20661-6-12, and 20666- 6-12; Airplanes Having Continental C125-1 or -2 Engines With Serial Numbers Below 1046-6-12 Except: 1034- 6-12, 1037-6-12 Through 1042-6-12, and 1044-6-12.

Compliance required immediately if engine has attained or passed 600-hour major overhaul period, but in any event not later than December 31, 1947, or 600 hours of operation, whichever occurs first.

A certain percentage of piston pins installed in engines of the above numbers and distributed as replacement parts are subject to failure without warning. The weakness of these pins cannot be detected by normal inspection methods. Piston pin breakage can result in complete engine failure. It is the owner's responsibility to avoid this risk by making the following change at the earliest possible time.

Replace piston pin assembly No. 22248-A1 (0.6875-inch inside diameter) with thick wall piston pin assembly No. 25121-A1 or 25262-A1 (0.5945-inch inside diameter). Supplies of the heavy wall pins are adequate so that immediate replacement can be effected.

(Continental Service Bulletin No. M47-9 covers this same subject.)

49-50-01 - Generator drive coupling disc <Recurring>

49-50-01 CONTINENTAL: Applies to All Continental C-75, C-85, C-90, C-125 and C-145 Engines Equipped With Generators, Except Those Engines Listed Below. (A-65 Series Engines Are No Longer Subjected to Compliance With This Note.)

To be accomplished prior to May 2, 1949, and upon each 100 hours of operation after inspection has been accomplished, or at major overhaul, as indicated.

To preclude possible engine failure as a result of disintegration of the generator drive coupling rubber disc, inspect and/or replace the disc as follows:

I. Old Type - Without Metal Retainer Cup. (1) Inspect rubber disc, P/N 22348 prior to May 2, 1949, and at 100-hour intervals after this inspection, and replace if deterioration or cracks are noted. Special attention should be given corners of slot to detect beginning of cracks or tears.

(2) Above periodic inspection may be discontinued by installing the improved type of coupling incorporating metal retainer cup P/N 352030.

II. Improved Type - With Metal Retainer Cup. (1) Rubber disc P/N 25120 must be replaced at major overhaul.

NOTE: Engines with the following serial numbers are excluded from the inspection requirements of this directive. However, if rubber disc P/N 25120 is incorporated, it must be replaced at major overhaul.

C-75: Serial No. 5257-7-12 and all higher numbers. C-85: Serial No. 30568-8-12 and all higher numbers. C-90: Serial No. 41132-8-12 and all higher numbers and including Nos. 41122 and 41124 through 41127. C-125: Serial No. 8108-8-2 and all higher numbers. C-145: Serial No. 3470-8-2 and all higher numbers. All "C" model engines reworked at Continental Motors Corp. since September 1, 1948.

(Description of generator drive couplings is contained in Continental Motors Corp. Service Bulletin Number M49-4. http://www.tcmlink.com/pdf2/SB95-3B.pdf , http://www.qaa.com/products/aircraft-alternators/alternator-drive-couplings/635796-alternator-drive-coupling ) This supersedes AD 49-47-01

81-07-06 - AC fuel pumps <Recurring>

81-07-06 TELEDYNE CONTINENTAL MOTORS: Amendment 39-4071. Applies to Continental A-65, A75, C75, C85, C90, A-100, C125, and O-200 series engines with AC fuel pumps, TCM part number 40585, 40695 or 631391 installed. Compliance required within 30 days after the effective date of this AD, or within the next 25 hours time in service after the effective date of this AD, whichever occurs first, unless already accomplished within the last 12 months and at intervals not to exceed 12 months after the last inspection. To prevent fuel starvation due to fuel flow restriction through the pump screen accomplish the following:

a. Remove safety wire and bolt from fuel pump top cover. Discard fiber washer under bolt.

b. Remove the fuel pump top cover. Discard cork cover gasket.

c. Remove fuel pump screen.

d. Inspect the fuel pump and fuel pump screen for contamination.

(1) If contaminated, clean fuel pump and fuel pump screen.

(2) If fuel pump is damaged by corrosion, replace with an applicable serviceable fuel pump.

(3) If fuel pump screen is damaged by corrosion or handling, replace with a serviceable fuel pump screen, TCM P/N 643913.

e. Reinstall fuel pump screen, fuel pump cover with new cork cover gasket, TCM P/N 643915 and new bolt gasket P/N 643914. Torque bolt to 30 +/- 5 inch-pounds.

f. Resafety wire fuel pump top cover bolt and check for leaks.

g. Make the appropriate maintenance record entry.

An equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. Teledyne Continental Motors Service Bulletin M81-8, dated March 9, 1981, pertains to this subject. This amendment becomes effective April 1, 1981.

93-22-05 - Carburetor air intake housing

93-22-05 TELEDYNE CONTINENTAL MOTORS: Amendment 39-8744. Docket 93-ANE-54.

Applicability: Teledyne Continental Motors (TCM) Model O-200A reciprocating engines with Engine Serial Numbers 256030 through 256037; and TCM C85, C90, O-200, and O-240 series reciprocating engines with carburetor air intake housing assemblies, Part Numbers (P/N) CE11141, CE11142, 639814, 639815, 641534, and Repair Kit Assemblies, P/N 641689, purchased after August 31, 1991, without a permanent ink stamp "CSB 93-13" located on the inside of the housing assembly. These engines are installed on but not limited to the following aircraft: ... Univair (Erco, Forney, Alon, Mooney) Model 415E, 415G, F-1, F-1A, A-2, and M-10.

Compliance: Required as indicated, unless accomplished previously.

To prevent engine failure due to a cracked air valve in the carburetor air intake housing assembly, accomplish the following:

(a) Within the next 5 hours time in service (TIS) after the effective date of this AD, inspect the carburetor air intake housing assembly in accordance with paragraph 2 of the Inspection Procedure section of TCM Critical Service Bulletin (CSB) No. 93-13, dated August 12, 1993.

(1) If the carburetor air intake housing assembly meets the requirements of Paragraph 2A of the Inspection Procedures of TCM CSB No. 93-13, dated August 12, 1993, no further action is required.

(2) If the carburetor air intake housing assembly meets the requirements of paragraph 2B of TCM CSB No. 93-13, dated August 12, 1993, inspect the carburetor air intake housing assembly for cracks. If cracks are found anywhere in the assembly, prior to further flight replace with a serviceable assembly.

(b) Thereafter, for assemblies that meet the requirements of paragraph 2B of TCM CSB No. 93-13, dated August 12, 1993, inspect the carburetor air intake housing assembly for cracks in accordance with Paragraphs 3 and 4 of the Inspection Procedure of TCM CSB No. 93-13, dated August 12, 1993, at intervals not to exceed 25 hours TIS since the last inspection. If cracks are found anywhere in the assembly, prior to further flight replace with a serviceable assembly.

(c) Inspect uninstalled carburetor air intake housing assemblies in accordance with paragraph (a) of this AD prior to installation.

(d) For the purpose of this AD, a serviceable carburetor air intake housing assembly is defined as:

(1) An assembly purchased on or before August 31, 1991; or (2) An assembly that meets the inspection criteria of paragraph (a)(1) of this AD; or

(3) An assembly with the following P/N's: (i) 653661, which supersedes CE11142; (ii) 653670, which supersedes 639815; (iii) 653675, which supersedes 641534; (iv) 653657, which supersedes 641689; or

(4) An assembly, P/N 641534, with a permanent ink stamp "CSB 93-13" located on the inside of the housing assembly. NOTE: The assemblies, P/N's CE11141 and 639814, have not been superseded, as these are assemblies with the air filter included, corresponding to airboxes, P/N's CE11142 and 639815.

(e) Replacement with a serviceable carburetor air intake housing assembly constitutes terminating action to the inspection requirements of this AD.

(f) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Atlanta Aircraft Certification Office. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Atlanta Aircraft Certification Office.

(g) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished.

(h) The inspections, and replacement, if necessary, shall be done in accordance with the following service document:

Document No.PagesRevisionDate
TCM CSB No 93-131-3 Total pages: 3OriginalAugust 12, 1993

This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Teledyne Continental Motors, P.O. Box 90, Mobile, AL 36601; telephone (205) 438-3411. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

(i) This amendment becomes effective December 14, 1993, to all persons except those persons to whom it was made immediately effective by priority letter AD 93-22-05, issued November 4, 1993, which contained the requirements of this amendment.

94-05-05 R1 - Rocker shaft bosses <Recurring>

94-05-05 R1 TELEDYNE CONTINENTAL ENGINES AND ROLLS-ROYCE, PLC: Amendment 39-9490. Docket 92-ANE-32. Revises AD 94-05-05, Amendment 39-8843.

Applicability: Teledyne Continental Motors (TCM) Model C75, C85, C90, C125, C145, O-200, O-300, and GO-300 series and Rolls-Royce, plc (R-R) C90, O-200 and O-300 series reciprocating engines, installed on but not limited to :

Univair (Erco) Models 415-D, E, and G; Univair (Forney) Models F-1 and F-1A; Univair (Alon) Model A-2 and Univair (Mooney) Model M-10 aircraft.

NOTE: This airworthiness directive (AD) applies to each engine identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For engines that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (d) to request approval from the Federal Aviation Administration (FAA). This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any engine from the applicability of this AD.

Compliance: Required as indicated, unless accomplished previously. To prevent engine power loss and engine failure, accomplish the following:

(a) At the next cylinder removal from the engine, or engine overhaul, whichever occurs first, after the effective date of this AD, inspect the cylinder rocker shaft bosses for cracks using one of the following methods, and if cracked replace with a serviceable cylinder: NOTE: Certain cylinder cracks may be repaired by FAA-approved repair stations specifically rated to do those repairs. (1) Fluorescent penetrant inspection, as follows: (i) The penetrant shall be a nontoxic, noncorrosive, highly fluorescent liquid capable of penetrating fine discontinuities and, for aluminum castings, conforming to Aerospace Material Specification (AMS) 3156. If a darkened enclosure is not used for examination, AMS 3157 penetrant shall be used.

(ii) The emulsifier shall be composed of suitable oil or oil-like components together with such additives as are necessary to provide a stable, nontoxic, noncorrosive, oil-miscible, oil-emulsifying solution. Emulsifier shall not be used when AMS 3156 is used.

(iii) The developer shall be a highly absorbent, nonfluorescent and nontoxic powder, capable of being used dry or a similar powder capable of being suspended in water. When the suspension is used, the powder shall be thoroughly mixed with water to a concentration, unless otherwise permitted, of not less than 0.2 lb per gallon and a uniform distribution maintained by mechanical agitation.

(iv) The penetrant, the emulsifier (if used) and the developer shall be checked as often as necessary to maintain proper control. The penetrant shall be discarded if it shows a noticeable loss in penetrating power or marked contamination or when wax begins to form on the sides of the tank and dip basket.

(v) A darkness booth or a similar darkness area with a filtered black light shall be provided. The black light shall be at least equal to that produced by a 100 watt mercury vapor projection spot lamp equipped with a filter to transmit wave lengths of between 3200 and 4000 Angstrom units and absorb substantially all visible light. The intensity of the light at normal working distance shall be as specified by the purchaser but in no case shall be lower than 580 micro-watts per square centimeter as measured with an appropriate black light meter.

(vi) All parts shall be cleaned and dried in such a manner as to leave them free from grease, oil, soaps, alkalis and other substances which would interfere with inspection. Vapor degreasing is generally suitable for this purpose.

(vii) Parts shall be immersed in the penetrant or shall be sprayed or brushed with the penetrant and shall be allowed to remain immersed in the penetrant or to stand for sufficient time to allow satisfactory penetration into all discontinuities. This time shall, unless otherwise specified, not be less than 5 minutes. The time for immersion or standing will depend upon the character and fineness of the discontinuities, the effectiveness of penetration increasing with time. Parts may be resprayed or re-immersed after standing to increase sensitivity and aid in removal of penetrant.

(viii) Parts shall be removed from the penetrant and cleaned thoroughly using a medium which will remove penetrant from the surface of parts; washing with water shall be used when the penetrant is water washable or when an emulsifying agent is applied to surfaces of parts to render the penetrant water washable. When emulsifiers are used, the parts shall be dipped in the emulsifier and removed slowly for draining or shall be sprayed with emulsifier and drained. Unless otherwise specified, the combined dipping and draining time shall be 1 to 5 minutes. When other than water washable penetrants are used, the penetrant shall be removed with a suitable cleaner or a suitable cleaner and lint-free cloths. During cleaning, the parts may be viewed under a suitable black light to ensure removal of the penetrant from the surface of the part. Excessive cleaning which would remove the penetrant from discontinuities shall be avoided.

(ix) When a wet developer is used, the developer shall be applied to the parts, immediately after washing, by immersing the parts in the tank containing the water-suspended powder or by spraying or flowing the suspension onto the parts. The suspension shall be suitably agitated either during or immediately prior to application to parts. Immersed parts shall be removed from the wet developer; excess developer shall be allowed to drain off all parts. Special care shall be taken to remove excess developer from pockets, recesses, holes, threads, and corners so that the developer will not mask indications. (x) When a dry developer or no developer is used, the parts shall be dried as thoroughly as possible by exposure to clean air. Drying of parts may be accomplished by evaporation at room temperature or by placing the parts in a circulating warm air oven or in the air stream of a hot air dryer. Excessive drying time or part temperatures higher than 80C (180F) should be avoided to prevent evaporation of the penetrant.

(xi) When a dry developer is used, the developing powder shall be applied uniformly over the areas of the parts to be inspected by either dusting or powder-box immersion.

(xii) After sufficient time has been allowed to develop indications, parts shall be examined under a black light. Examination shall be made in a darkened enclosure unless AMS 3157 penetrant is used, in which case examination may be made under normal shop lighting but shaded from direct sunlight.

(xiii) When greater sensitivity is desired, the parts may be heated to 65-85C (150-185F) before immersion in the penetrant and/or before black light examination. To prevent evaporation, preheated parts shall remain fully immersed in the penetrant until cooled.

(xiv) Parts shall be cleaned, as necessary, to remove penetrant and developer.

(xv) Interpretation of the indications revealed by this inspection procedure and final disposition of the parts shall be the responsibility of only qualified personnel having experience with fluorescent penetrant inspection.

(xvi) Parts having discontinuities (cracks) shall be rejected.

(2) Dye penetrant inspection, as follows: NOTE: Military Specification MIL-I-6866 and American Society of Testing Materials specifications ASTM E1417-93 and E165-9 contain additional information on dye penetrant inspection processes.

(i) Preparation: clean and dry all parts in such a manner as to leave the surfaces free from grease, oil, soaps, alkalis, and other substances which would interfere with inspection. Vapor degreasing is generally suitable for this purpose.

(ii) Penetrant Application Procedure: after preparation, spray or brush the parts with the penetrant, and allow to stand for not less than 5 minutes. The effectiveness of the penetrant increases if left standing for a longer time, as the penetrant will reach finer discontinuities.

(iii) Penetrant Cleaning: clean the parts thoroughly using a medium which will remove penetrant from the surfaces of parts; wash with water when the penetrant is water soluble. When other than water soluble penetrants are used, the penetrant shall be removed with a suitable cleaner. Avoid excessive cleaning which would remove the penetrant from discontinuities.

(iv) Drying: dry the parts as thoroughly as possible. Drying of parts may be accomplished by evaporation at room temperature or by placing the parts in a circulating warm air oven or in the air stream of a hot air dryer. Avoid excessive drying time or drying temperatures above 75C (165F) to prevent excessive evaporation of the penetrant. If heat is used for drying parts, cool parts to approximately 50C (120F) before proceeding to the developing procedure.

(v) Developing: apply the developer to the dry parts as lightly and as evenly as possible, using as thin a coating of developer as is possible. A translucent film is adequate. Mix wet developer by agitation immediately prior to applying it. After applying the developer, take care that no penetrant indication is disturbed or obliterated in subsequent handling.

(vi) Examination: examine the developed penetrant indications in accordance with the dye penetrant manufacturer's instructions. Examine parts for indications of discontinuities open to the surface.

(vii) Final cleaning: clean the parts following the inspection to remove penetrant and developer. NOTE 1: Caution: because of differences among penetrants, take care to ensure that the final cleaner, the penetrant, the penetrant remover, and the developer are suitable for use with each other. NOTE 2: Caution: all penetrant materials should be kept as free from moisture as possible. NOTE 3: Caution: most penetrants, cleaning agents, and developer suspensions are low flash point material; use caution to prevent fires.

(3) Etching inspection, as follows:

(i) For TCM C75, C85, C90, O-200 and R-R C90 and O-200 series engines, in accordance with paragraph 13-7 of TCM Overhaul Manual Form X-30010, dated January 1984.

(ii) For TCM C125, C145, O-300, GO-300 and R-R O-300 series engines, in accordance with paragraphs 5(b)(1), 5(b)(2), and 5(b)(3) of TCM Overhaul Manual Form X-30013, dated June 1982.

(b) At the next cylinder removal from the engine, or engine overhaul, whichever occurs first, after the effective date of this AD, dimensionally inspect cylinders for looseness of the rocker shaft in accordance with page 22, paragraph 5, and Table IX of TCM Overhaul Manual Form X-30013, dated June 1982, for TCM C125, C145, O-300, GO-300 and R-R O-300 series engines, and the dimensions table in paragraph 13-8 of TCM Overhaul Manual Form X-30010, dated January 1984, for TCM C75, C85, C90, O-200 and R-R C90 and O-200 series engines; as applicable.

(1) Cylinders that do not exhibit dimensional looseness of the rocker shaft beyond the limits specified in the applicable TCM overhaul manual may be returned to service.

(2) For cylinders that exhibit dimensional looseness of the rocker shaft, beyond the limits specified in the applicable TCM overhaul manual, accomplish the following:

(i) Replace with a serviceable cylinder; or

(ii) Install bushings in accordance with the instructions on page 27 of TCM Overhaul Manual, Form X-30013, dated June 1982, for TCM C125, C145, O-300, GO-300 and R-R O-300 series engines; or the instructions on page 85 of TCM Overhaul Manual Form X-30010, dated January 1984, for TCM models C75, C85, C90, O-200 and RR C90 and O-200 series engines, as applicable.

(iii) After repairing a cylinder perform an additional inspection of the cylinder rocker shaft bosses for cracks using fluorescent penetrant, dye penetrant, or etching methods, and replace, if necessary, with a serviceable cylinder.

(c) Thereafter, at each subsequent cylinder or engine overhaul, reinspect cylinder rocker bosses and rocker shafts in accordance with paragraphs (a) and (b) of this AD.

(d) An alternative method of compliance or adjustment of the initial compliance time that provides an acceptable level of safety may be used if approved by the Manager, Atlanta Aircraft Certification Office. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta Aircraft Certification Office.

(e) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the aircraft to a location where the requirements of this AD can be accomplished.

(f) This amendment becomes effective on February 13, 1996.



Propellors, McCauley 1A90CF or 1B90CM


Propellors, Sensenich M76AK-2

2005-14-11 - Certain props returned to service by Southern California Propeller Service, of Inglewood, CA.

2005-14-11 Hartzell Propeller, Inc., McCauley Propeller Systems, and Sensenich Propeller Manufacturing Company, Inc. Propellers: Amendment 39-14188. Docket No. 2003-NE-53-AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective August 17, 2005.

Affected ADs

(b) None.

Applicability

(c) This AD applies to the Hartzell Propeller, Inc., McCauley Propeller Systems, and Sensenich Propeller Manufacturing Company, Inc. propeller models last returned to service by Southern California Propeller Service of Inglewood, CA., listed in the following Table 1:

Table 1.--Applicable Propeller Models

Hartzell Propeller, Inc. ()HC()(2,3,4)Y()(). ()HC()(2,3,4)(X,V,MV,W,Z,P,R) (F,G,L,K,R,20,30,31)(). ()HA()(). HCB(3,4)(M,P,R,T)(A,N,P)(). HC(D,E)(4,5)(A,B,N,P)(). McCauley Propeller Systems ()2()()3()C()()()(): All constant speed two-bladed propeller models. ()3()()3()C()()()(): All constant speed three-bladed propeller models. 1()()()()/(): All metal propeller models. Sensenich Propeller Manufacturing Company, Inc. All metal propeller models.

(d) These actions are against propeller models returned to service by Southern California Propeller Service. Southern California Propeller Service is not to be confused with propeller repair stations known as California Propeller or as Propeller Service of California. Southern California Propeller Service was issued Air Agency Certificate number of VXSR617L in 1992, which was revoked in June of 1998.

(e) For Hartzell and McCauley propeller models listed in Table 1 of this AD, any letter or number (or lack of a letter or number) could appear where open parentheses are shown in the model number. Model numbers could show any combination of letters or numbers where the model number shows parentheses with a series of numbers or letters.

(f) For propeller models listed in Table 1 of this AD, that have been overhauled since being returned to service by Southern California Propeller Service by an authorized repair station other than Southern California Propeller Service, no further action is required.

Unsafe Condition

(g) This AD results from the investigation of a failed propeller blade and subsequent inspections of various propeller models returned to service by Southern California Propeller Service, of Inglewood, CA. We are issuing this AD to prevent blade failure that could result in separation of a propeller blade and loss of control of the airplane.

Compliance

(h) You are responsible for having the actions required by this AD performed within 10 hours time-in-service after the effective date of this AD.

Required Actions

(i) Perform the actions specified in paragraph (j) of this AD on propeller models listed in Table 1 of this AD. You can find information on performing the actions in the applicable propeller manufacturer's service documentation.

(j) Perform the following actions:

(1) Disassemble,

(2) Clean,

(3) Inspect for the following:

(i) Cracks,

(ii) Corrosion or pits,

(iii) Nicks,

(iv) Scratches,

(v) Blade minimum dimensions,

(vi) Unapproved localized heating of blade,

(vii) Unapproved use of helicoil inserts in actuating pin holes,

(viii) Improperly drilled actuating pin holes,

(ix) Chemical conversion coat or paint or both applied over corrosion,

(x) Lack of chemical conversion coating,

(xi) Lack of paint on internal surfaces,

(xii) Bolts incorrectly torqued,

(xiii) Incorrect parts,

(xiv) Incorrect installation of parts,

(xv) Reinstallation of parts intended for one-time use, and

(xvi) Lack of proper shot peening.

(4) Repair and replace with serviceable parts, as necessary,

(5) Reassemble and test.

Alternative Methods of Compliance

(k) The Manager, Chicago Aircraft Certification Office, has the authority to approve alternative methods of compliance (AMOCs) for this AD if requested using the procedures found in 14 CFR 39.19.

Special Flight Permits

(l) Under 14 CFR 39.23, we are limiting the special flight permits for this AD by not allowing any flights with apparent cracks in propellers.

Related Information

(m) Special Airworthiness Information Bulletin No. NE-01-19, dated March 20, 2001, pertains to the subject of this AD.



Appliances.
81-15-03 - Brackett air filters

81-15-03 (BRACKETT AIRCRAFT COMPANY, INC. Brackett Aircraft Specialties, Inc.): Amendment 39-4160. Applies to Brackett Aircraft Company, Inc., engine inlet air filters installed in accordance with Supplemental Type Certificate (STC) SA693CE and STC SA71GL on the following aircraft:

Beech A65, 70, 65-B80, 65-88, C-23, A-24R, and B-24R; Bonanza 33, 35, and 36, all models; Cessna Model 120, 140, 140A, 150, 150B, 150C, 150D, 150E, 150F, 150G, 150H, 150J, 150K, 150L, 150M, A150L, and A150M, 170, 170A, 170B, 172, 172A, 172B, 172C, 172D, 172E, 172F, 172G, 172H, 172I, 172K, 172L, and 172M, 177, 177A, 177B, 177RG, and F177RG, 180C, 180D, 180E, 180F, 180G, 180H, 180J, 180K, 182B, 182C, 182D, 182E, 182F, 182G, 182H, 182J, 182K, 182L, 182M, 182N, 182P, 182Q, 185, 185A, 185B, 185C, 185D, 185E, and A185F, 210A, B, C, D, E, and 310A, B, C, D, F, G, H, I, J, K, L; Consolidated Aeronautics (Lake) LA4-200; Grumman American Model AA-1, AA-1A, AA-1B, and AA-5; Mooney M18C, M20, M20A, M20B, M20C, M20D, and M20G; Piper Model PA-20, PA-20-115, and PA-20-135, PA-23-150, 160, PA-24-180 to S/N 1477, PA31, 31-300, 31-350; and Varga (Shinn) Model 2150A, certificated in all categories.

Compliance required as indicated, unless already accomplished.

To prevent possible failure of the aluminum air filter retainer screen or gaskets with potential ingestion of the screen, filter element and/or gasket particles into the carburetor throat, which could result in partial or complete loss of engine power, accomplish the following:

(a) Within 25 hours of time in service after the effective date of this AD, inspect aircraft as identified in Brackett Service Bulletin No. 3, Revision 1, dated March 1, 1979, or No. 6, Revision 1, dated June 29, 1981, as applicable, equipped with the Brackett Aircraft Company, Inc. engine inlet air filters, to determine

(1) whether the air filter retainer screen is aluminum or steel, and

(2) whether or not certain air filter frames incorporate a gasket retainer. Brackett filter assemblies Part Number BA 100, BA 2310, BA5710, BA 7110, BA 7210, BA 7310, BA 7410 and BA 7510 are required to have a gasket retainer incorporated. The gasket retainer may be a gasket retainer strip kit installed in accordance with Brackett Service Bulletin No. 5, dated July 28, 1980, or an extruded lip which is 1/32 inch high and an integral part of the filter frame furnished by Brackett Aircraft Company, Inc.

NOTE: The aluminum air filter retainer screen can be identified by any one of the following:

The screen has diamond shaped mesh with openings 1-3/4 inch x 3/4 inch; aluminum screen is not magnetic; the date of manufacture was ink stamped on each retainer and may still be legible. Only retainers dated August 1978 and earlier have aluminum mesh screen.

NOTE: The steel retainer screen can be identified by any one of the following:

The screen is 1/8 inch diamond mesh; the screen is magnetic; date of manufacture is ink stamped on each retainer and may still be legible. Retainers dated September 1978 and later have steel mesh screen.

(b) A determination that the air filter retainer screen is steel and that a gasket retainer is incorporated in the filter frame constitutes terminating action for this AD.

(c) Upon determination that the retainer screen is aluminum, visually inspect the aluminum retainer assembly for cracks or failed areas.

(1) If cracks or failed areas are found, prior to further flight, replace the aluminum retainer screen assembly with a steel screen assembly kit in accordance with Brackett Service Bulletin No. 3, Revision 1 dated March 1, 1979 or No. 6, Revision 1 dated June 29, 1981, as applicable. Each model air filter requires that a different Brackett kit be installed to comply with this AD.

(2) If cracks or failed areas are not found, the air filter assembly may be temporarily returned to service. Remove retainers with aluminum screen from service prior to the accumulation of 100 hours additional time in service.

(d) After the inspection required in Paragraph (a) and upon determination that a gasket retainer is not incorporated in the filter retainer, prior to the accumulation of 25 additional hours of service, install gasket retainer strips in accordance with Brackett Service Bulletin No. 5 dated July 28, 1980.

Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate aircraft to a base for the accomplishment of inspections or modifications required by this AD.

Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Engineering and Manufacturing Branch, FAA Western Region.

The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive, who have not already received these documents from the manufacturer, may obtain copies upon request to: Brackett Aircraft Company, Inc., 5015 Roadrunner Drive, Falcon Field, Mesa, Arizona 85205. These documents may also be examined at: FAA Western Region Office, 15000 Aviation Boulevard, Hawthorne, California 90261 and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. A historical file on this AD, which includes the incorporated material in full, is maintained by the FAA at its Headquarters in Washington, D.C. and at FAA Western Region Office.

This supersedes AD 78-25-05, Amendment 39-3365 (43 FR 57865).

This amendment becomes effective July 20, 1981.

96-09-06 - Brackett air filters

BA-4106 Univair Models (Alon) A-2, A2-A, (Forney) F-1, F-1A, and (Mooney) M10;

NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (f) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Compliance: Required within the next 100 hours time-in-service (TIS) after the effective date of this AD, or within the next 100 hours TIS after the last inspection accomplished in accordance with AD 95-03-02, whichever occurs first, and thereafter as indicated in the body of this AD, unless already accomplished in accordance with paragraph (c) of this AD.

To prevent gasket particles from entering the carburetor because of air filter gasket failure, which could result in partial or complete loss of engine power, accomplish the following:

(a) Inspect (visually) the inside and outside of the air filter frame for gasket looseness, movement, or deterioration in accordance with Brackett Document I-194, dated March 16, 1994. Continue this repetitive inspection at intervals not to exceed 100 hours TIS, until accomplishment of the terminating action required in paragraph (c) of this AD.

(b) If the gasket is found to be damaged, prior to further flight, replace the air filter assembly with one having a retaining lip in accordance with the Brackett INSTALLATION INSTRUCTION SHEET corresponding to the new air filter assembly part number that is applicable to the owner/operator's particular model of airplane: Air Filter Assembly Replace with Assembly Instruction Sheet BA-2010 BA-2010 Revision A BA-2004, dated 6/6/95 BA-4106 BA-4106 Revision D BA-4105, dated 6/15/95 BA-4106-1 BA-4106-1 Revision A RM-1, dated 7/6/95 BA-4210 BA-4210 Revision B BA-4205, dated 6/14/95 BA-5110 BA-5110 Revision H BA-5105, dated 5/8/95 BA-5110A BA-5110A Revision D BA-5111, dated 5/8/95 BA-6110 BA-6110 Revision C BA-6105, dated 6/5/95 BA-8910 BA-8910 Revision B BA-8910-3, dated 6/6/95 AAF-117 BA-4106 Revision D BA-4105, dated 6/15/95 AAF-118 BA-5110 Revision H BA-5105, dated 5/8/95

(c) Within the next 500 hours TIS after the effective date of this AD, replace the air filter assembly as a terminating action to this AD in accordance with the Brackett INSTALLATION INSTRUCTION SHEET corresponding to the new air filter assembly part number that is applicable to the owner/operator's particular model of airplane as specified in paragraph (b) of this AD.

(d) The replacement in paragraphs (b) and (c) is considered terminating action for the repetitive inspection required by this AD.

(e) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished.

(f) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Los Angeles Aircraft Certification Office, FAA, 3960 Paramount Boulevard, Lakewood, California 90712. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Los Angeles Aircraft Certification Office.

NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles Aircraft Certification Office.

(g) Alternative methods of compliance approved in accordance with AD 95-03-02 (superseded by this action) are considered approved as alternative methods of compliance with this AD.

(h) The inspections and replacements required by this AD shall be done in accordance with Brackett Air Filter Document I-194, dated March 16, 1994 and with the Brackett INSTALLATION INSTRUCTION SHEET corresponding to the new air filter assembly part number that is applicable to the owner/operator's particular model of airplane referenced as specified in paragraph (b) of this AD. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Brackett Aircraft Company, Inc., 7045 Flightline Drive, Kingman, Arizona 86401. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., 7th Floor, suite 700, Washington, DC.

(i) This amendment supersedes AD 95-03-02, Amendment 39-9139.

(j) This amendment (39-9580) becomes effective on June 7, 1996




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