|
2010-24-06: We are superseding an existing airworthiness directive (AD) that applies to the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an airworthiness authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as
Subsequent to accidents involving Fuel Tank System explosions in flight * * * and on ground, * * * Special Federal Aviation Regulation 88 (SFAR88) * * * required a safety review of the aircraft Fuel Tank System * * *.
* * * * *
Fuel Airworthiness Limitations are items arising from a systems safety analysis that have been shown to have failure mode(s) associated with an `unsafe condition' * * *. These are identified in Failure Conditions for which an unacceptable probability of ignition risk could exist if specific tasks and/or practices are not performed in accordance with the manufacturers' requirements.
* * * * *
Weare issuing this AD to require actions to correct the unsafe condition on these products.
|
|
98-07-08: This amendment adopts a new airworthiness directive (AD) that is applicable to all IAI, Ltd., Model 1125 Westwind Astra and Astra SPX series airplanes. This action requires disabling of the baggage compartment electrical heating blankets. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent overheating of the electrical heating blankets, and consequent increased risk of fire in the baggage compartment.
|
|
98-07-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires replacement of the main landing gear (MLG) trunnion fittings with reinforced trunnion fittings. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent collapse of the MLG due to fatigue cracking of the MLG trunnion fittings.
|
|
79-22-01: 79-22-01 BELLANCA: Amendment 39-3596. Compliance is required within the next 30 days or 10 hours of aircraft time in service, whichever occurs first, after the effective date of this AD, unless already accomplished. To prevent exhaust system cracking, accomplish the following on Bellanca Model 7ECA (S/N 985-74 thru 1319-79), 8KCAB (S/N 120-74 thru 550-79 equipped with Lycoming AEIO-360 series engine), and 8GCBC(S/N 1-74 thru 323-79) aircraft:
1. Remove the upper and lower engine cowling.
2. Inspect exhaust system with particular attention to the welded area between the riser tube and the exhaust flange, for cracks, fractures or evidence of exhaust leakage. Remove the heater shroud and inspect the muffler body for cracks, fractures or evidence of exhaust leakage. If any exhaust system component is cracked or otherwise damaged, remove the exhaust system and repair/replace damaged parts in accordance with FAA Advisory Circular 43.13-1A.
3. Loosen exhaust port studnuts several turns; check bead clamps for tightness such that the clamps cannot rotate on the exhaust system with hand pressure. The riser flanges (1) must have equal spacing to the exhaust port pad at both studs (a small amount of flange bow is acceptable), (2) must be free to move up and down on the exhaust port studs without binding and (3) must all contact the exhaust port pads together.
4. If any of the alignment checks are unsatisfactory, determine the cause for the misalignment and repair or replace the part as required.
5. Assemble exhaust system and install on engine with loose exhaust port stud nuts and bead clamp bolts. Torque exhaust port stud nuts to the correct value. Tighten bead clamp bolts until clamps secure risers to exhaust system but allow clamps to rotate with hand pressure; the bead clamps should not be rigidly clamped to the tubes but should be able to rotate on the tubes with moderate hand pressure on the clamp assembly. NOTE: Torque all exhaust port stud nuts evenly and tighten bead clamp bolts evenly to insure uniform loads within the exhaust system parts; torquing bolts individually can cause very large stresses.
6. Inspect exhaust system for proper clearance between ducts, wiring, controls, etc. before reinstallation of the cowling. Install lower cowling and inspect for proper clearance between exhaust outlet and cowl.
7. Reinstall the lower and upper engine cowling.
Bellanca Service Letter Number C-138 covers this same subject.
Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Great Lakes Engine..
This amendment becomes effective October 29, 1979.
|
|
98-06-25: This amendment adopts a new airworthiness directive (AD) that applies to Fairchild Aircraft Inc. (Fairchild) Models SA226-AT, SA226-TC, SA227-AC, and SA227-AT airplanes. This action would require inspecting the cargo door lower belt frames at the cargo latch receptacles for cracks in the belt frames, repairing any cracks, and reinforcing the cargo door lower belt frames by installing doublers. The AD is the result of a decompression incident during flight caused by fatigue at the bottom of the cargo door on a Fairchild Model SA226-TC. The actions specified by this AD are intended to prevent the failure of the cargo door in flight, which could cause decompression injuries to passengers and substantial structural damage to the airplane.
|
|
2017-10-22: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, and -900 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the web lap splices in the aft pressure bulkhead are subject to widespread fatigue damage (WFD). This AD requires repetitive inspections of the web lap splices in the aft pressure bulkhead for cracking of the fastener holes, and repair if necessary. We are issuing this AD to address the unsafe condition on these products.
|
|
2017-09-02: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Deutschland GmbH Helicopters (Airbus Helicopters) Model MBB-BK 117 C-2 and MBB-BK 117 D-2 helicopters. This AD requires installing rivets to the air inlet cover rings (rings). This AD was prompted by reports of rings detaching. The actions of this AD are intended to prevent the unsafe condition on these products.
|
|
79-01-01: 79-01-01 BEECH: Amendment 39-3386. Applies to the following models and serial number airplanes, certificated in all categories, except those that have previously complied with AD 74-13-02:
MODELS
SERIAL NUMBERS
ITEM NUMBERS
(Refers to Items in Table I)
F33A
CE-447 through CE-684
(1), (2)
F33A
CE-372
(2)
F33C
CJ-31 through CJ-128
(1), (2)
G33
CD-1292 through CD-1304
(1), (2)
35-C33
CD-970
(1), (2)
35-C33, 35-C33A
CD-1066 & CE-62
(2)
35-B33
CD-700
(2)
V35B
D-9478 through D-9480,
D-9482 through D-9531,
D-9533 through D-9536
and D-9539 through D-9968
(1)
A36
E-323
(2)
A36
E-441 through E-954
(1), (2)
D55 & D55A
TE-485, TE-615,
TE-703 and TE-710
(2)
E55 & E55A
TE-790, TE-911
(2)
E55 & E55A
TE-905, TE-923 through TE-937,
TE-939, TE-940, TE-942, and
TE-943 through TE-1084
(1), (2)
56TC
TG-78 and TG-83
(2)
58 & 58A
TH-49, TH-77, TH-114,
TH-180, TH-217, TH-324
(2)
58 & 58A
TH-145, TH-340 and
TH-343 through TH-779(1), (2)
58P & 58PA
TJ-2 through TJ-97
(1), (2)
58TC & 58TCA
TK-1 through TK-37
(1), (2)
65-B80
LD-441 through LD-511
(1), (3), (5), (6), (7)
70
LB-31 through LB-35
(1), (3), (5), (6), (7)
B90 & C90
LJ-500 through LJ-706
(1), (3), (5), (6), (7)
E90
LW-1 through LW-209
(1), (3), (5), (6), (7)
95-A55
TC-241
(1)
95-B55 & 95-B55A
TC-661 and TC-1510
(2)
95-B55 & 95-B55A
TC-1570 through TC-2011
(1), (2)
95-C55 & 95-C55A
TE-271
(2)
95-C55 & 95-C55A
TE-415
(1)
99, 99A, A99A, B99
U-134 through U-164
(1), (3), (4), (5), (6), (7)
100 & A100
B-61 through B-178,
B-180 through B-204
and B-206 through B-231
(1), (3), (4),
(5), (6), (7)
B100
BE-1 through BE-19
(1), (3), (4), (5), (6), (7)
200
BB-2 through BB-185,
& BB-187 through BB-199
(3), (4), (8),
(9), (10)
COMPLIANCE: Required as indicated unless already accomplished.
To assure continued structural integrity of certain screws in the airplane control system, in accordance with instructions set forth herein and in Beechcraft Service Instructions No. 0629- 150, Revision II or later approved revisions, accomplish the following:
A) Within 100 hours time-in-service after the effective date of this AD:
For affected models and serial numbers, determine those Item Numbers applicable thereto by referring to the column above entitled "Item Numbers". Next, determine the number, type and location of screws by referring to Table I of this AD (see below). Replace each screw at the specified location except that an existing screw need not be replaced if inspection shows that the head has at least one raised or depressed "X" mark. Replace the screws one at a time at the hinge brackets to retain original alignment of the bracket.
B) Any equivalent means of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region.
TABLE I
Item 1. Two AN502-10-10 screws securing each hinge bracket at leading edge of rudder or ruddervator.
Item 2. Two AN502-10-10 screws securing each hinge bracket at leading edge of elevator.
Item 3. Two AN502-10-12 screws securing elevator control cables to forward bellcrank under pilot's compartment left floorboard.
Item 4. Two AN503-8-8 screws securing elevator control cables to aft bellcrank in fuselage tail section.
Item 5. Two AN503-8-10 screws securing rudder control cables to forward bellcrank under pilot's compartment floorboard aft of left rudder pedals.
Item 6. Two AN503-8-6 screws securing rudder control cables to aft bellcrank in the fuselage tail section.
Item 7. Two AN503-8-6 screws securing aileron control cables to bellcrank under floorboard just forward of the rear spar.
Item 8. Two AN503-8-8 screws securing rudder control cables to forward bellcrank under pilot's compartment floorboard aft of left rudder pedals.
Item 9. Two AN503-8-8 screws securing rudder control cables to the aft quadrant assembly in the fuselage tail section.
Item 10. Two AN503-8-8 screws securing aileron control cables to bellcrank under floorboard just forward of the rear spar.
This AD supersedes AD 74-13-02, Amendment 39-1874 (39 FR 20784).
NOTE: Scheduling accomplishment of this Airworthiness Directive simultaneously with accomplishment of Airworthiness Directive No. 78-22-05 will result in a savings of man-hours.
This amendment becomes effective January 8, 1979.
|
|
63-22-01: 63-22-01 GRUMMAN: Amdt. 632 Part 507 Federal Register October 25, 1963. Applies to Model G-164 Aircraft Serial Numbers 1 through 220.
Compliance required within the next 100 hours' time in service after the effective date of this AD, unless already accomplished.
To prevent damage to fuel and oil lines from spray pump fan blades, rivet two 0.063 inch thick 2024-T3 aluminum alloy sheets approximately 6 inches wide by 18 and 28 inches long each, to the left and right lower accessory cowl panels using at least 10 and 16 AD 4 type rivets respectively. Center the plate's long dimension opposite the spray pump fan blade arc.
(Grumman Aircraft Engineering Corporation Model G-164 Service Bulletin No. 23, dated June 17, 1963, pertains to this same subject and also lists the availability of Grumman armor plates P/N's A1624-111 and -113.)
This directive effective October 25, 1963.
|
|
2017-09-05: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS332C, AS332C1, AS332L, AS332L1, AS332L2, and EC225LP helicopters. This AD requires repetitively checking screws in the emergency flotation gear. This AD is prompted by a report that a screw ruptured on a Model AS332 helicopter's emergency flotation gear. These actions are intended to correct an unsafe condition on these products.
|