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2004-12-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Model BAe.125 series 800A, 800A (C-29A), and 800B airplanes; and Model Hawker 800 airplanes, that requires a one-time inspection of certain wire bundles for discrepancies and related corrective action. This action is necessary to find and fix chafing and damage to the wire bundles, which could result in electrical arcing and heat damage in a potential fuel zone and possible fire or explosion in the fuel tank. This action is intended to address the identified unsafe condition.
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2021-19-15: The FAA is superseding Airworthiness Directive (AD) 2019-01- 08, which applied to certain The Boeing Company Model 777-200, -200LR, -300, and -300ER series airplanes. AD 2019-01-08 required modifications for galley mounted attendant seat fittings. This AD was prompted by a report that showed a non-compliance exists on some in-service galley attendant seat fitting installations, and a determination that additional airplanes are subject to the unsafe condition. This AD requires modifications for galley mounted attendant seat fittings. The FAA is issuing this AD to address the unsafe condition on these products.
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66-30-02: 66-30-02 BOEING: Amdt. 39-316 Part 39 Federal Register December 13, 1966. Applies to Model 727 Series Airplanes. \n\n\tCompliance required as indicated, unless already accomplished. \n\n\tTo minimize fuselage fire hazards resulting from fuel line ruptures during excessively hard landings involving structural damage, accomplish the following; \n\n\t(a)\tWithin the next 1,500 hours' time in service after the effective date of this AD, remove aluminum fuel lines, P/N 69-16668-1, in the fuselage (three places) located between Body Stations 887 and 1183, and replace with flexible fuel lines, P/N 10-60536-2, in accordance with Boeing Service Bulletin No. 28-26, dated April 27, 1966, or later FAA-approved revision or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\t(b)\tWithin the next 7,000 hours' time in service after the effective date of this AD, reroute the generator electrical leads (three places) and encase in teflon tubing between Fuselage Stations 850 and 1183 in accordance with Boeing Service Bulletin No. 24-30, revised May 18, 1966, or later FAA-approved revision, or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis directive effective January 12, 1967.
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2021-26-09: The FAA is adopting a new airworthiness directive (AD) for certain Brantly Helicopters Industries U.S.A. Co., Ltd., Model 305 helicopters and Brantly International, Inc., Model B-2, B-2A, and B-2B helicopters. This AD was prompted by a report of a crack in the tail rotor (T/R) hub. This AD requires repetitive inspections of the T/R hub and depending on the results, removing the T/R hub from service. The FAA is issuing this AD to address the unsafe condition on these products.
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77-13-17: 77-13-17 MCCAULEY PROPELLERS: Amendment 39-2943. Applies to the following two-bladed and three-bladed constant speed "Non-Feathering" and "Full Feathering" type McCauley propellers, which were modified by Hoosier Aircraft Accessory, Inc., Indianapolis, Indiana during the period of December 8, 1972 thru June 30, 1975. These propellers are installed on, but not limited to the aircraft models listed below.
Constant Speed "Non-Feathering" Propellers
Model
(Note 1)
Hub Serial No.
(Note 2)
Aircraft Model
(Note 3)
(A) Two Bladed
2A34C22 (*)
713477
Maule M-5-220C;
714270
M-4-180C, S, T
D2A34C67 (*)
692205
Cessna R172E, -F, -G, and -H; FR172E, -F, -G, and - H, Maule M-4-210C, -210S, - 210T; M-5-210C
(B) Three Bladed
D3A32C77 (*)
661184
Cessna P206A, TP206A,
726348
210F, and T210F
D3A32C88 (*)
724926
Cessna P206, P206A, - B, -C, -D, -E;
Cessna TP206A, -B, - C, -D, -E;
TU206F (S/N U20602200 and up)
Cessna 210F, -G, -H, - J, -K, -L;
T210G, -H, -J, -K, and -L
Constant Speed "Full-Feathering" Propellers
Model
(Note 1)
Hub Serial No.
(Note 2)
Aircraft Model
(Note 3)
(A) Two Bladed
D2AF34C30 (*)
700468
Beech 58, 58A
or
701342
2AF34C30 (*)
705241
705242
D2AF34C52 (*)
728611
Cessna 310I
730034
730556
2AF34C55 (*)
682955
Beech 95-55, 95-A55,
684789
95-B55, 95-B55A
697330
95-B55B, 95-C55,
713643
95-C55A, D-55, D- 55A,
726670
E-55, E-55A Series
728131
728141
D2AF34C59 (*)
642020
Cessna 337; 337A, -B, -C,
or
723964
-D, -E, and -F Series
2AF34C59 (*)
Burns BA42
D2AF34C61 (*)
66394
Cessna 336; 337, 337A,
or
675836
-B, -C, -E and -F
2AF34C61 (*)
683257
Series; T337B, -C, -D,
684839
-E and -F Series; F337E,
686708
F337F
691475
727098
736922
741911
745073
750643
D2AF34C71 (*)
685300
Cessna 310P, -Q, -R;
694684
T310P, -Q; 320D, -E and340
D2AF34C81 (*)
651926
Cessna 310J, E310J,
671750
310K, 310L, and 310N
672239
673494
682298
741088
741102
D2AF34C91 (*)
722029
Cessna T337B, T337C, T337D,
T337E and T337F; and FT337E, FT337F
(B) Three Bladed
3AF34C74 (*)
661086TR
Cessna 411, 411A
662363TR
692379
3AF32C75 (*)
702047
Beech 95-C55, 95- C55A,
702051
D55, D55A, E55, and E55A
D3AF32C80 (*)
66986
Cessna 310K, -L, and - N
or
661000
Colemill Executive 600
3AF34C80 (*)
665633
(STC SA518SO - Cessna
738455
310J, -K, -L, -N
738586
Conversion)
744076
3AF32C87 (*)
68588
Cessna 310P, -Q, -R;
683600
TP310P, -Q, -R; 320D,
683602
-E, -F; 340
685410
Colemill Executive 600
692770
(STC SA518SO Cessna
694218
310I Conversion)
705807
Riley (STC SA1181SW-
710281
Cessna 340 Conversion)
712311
713792
723589
737625
737974
739577
743892
743893744411
746518
748219
3AF34C92 (*)
682034
Cessna 421, 421A, and -B
or
682054
3AF32C92 (*)
685899
686191
720868
721301
733370
734880
3AF32C93
722256
Cessna 414
722257
Notes:
(*) - Denotes suffix letter(s). Some models have one or more suffix letter designations, others have none.
(1)&(2) - Propeller model and hub serial numbers are stamped on the side of the propeller hub. The listing of hub serial numbers refers to specific hub serial numbers not series. In the event a spinner is installed, the spinner should be removed to check the model and hub (S/N) designations. The aircraft's records should likewise be checked to endure that the model and hub serial number coincide with the records. In the event an error is noted, the records should be corrected accordingly. Prior to further flight, spinners should be reinstalled where applicable.
(3) - If no listing of aircraft serial numbers is indicated, applies to all applicable serial numbers of a particular aircraft model or series.
Compliance required within the next 25 hours' time in service after the effective date of this AD, unless already accomplished.
To preclude the possibility of blade actuating pin failures resulting from using an incorrect actuating pin, or improper rework of the ferrules and installation of the blade actuating pins and washers (i.e., a blind actuating pin hole not tapped to the proper depth can cause stripped threads on the ends of the actuating pin resulting in severe stress and may prevent actuating pin from seating properly on the washer), accomplish the following:
A. Disassemble the propeller and inspect the blade actuating pins, washers McCauley Service Bulletins No. 99 dated December 8, 1972, No. 99-1 dated December 14, 1972, No. 99-2 dated April 23, 1973, and No. 99-3 dated August 11, 1975, or later Federal Aviation Administration approved revisions.
B. Prior to further flight repair or replace as necessary, any improperly installed blade actuating pins, washers and ferrules, and reassemble the propeller in accordance with McCauley Service Bulletins No. 99 dated December 8, 1972, No. 99-1 dated December 14, 1972, No. 99-2 dated April 23, 1973, No. 99-3 dated August 11, 1975, and Service Manuals 710930 and 720415, or later Federal Aviation Administration approved revisions.
C. When the above propellers are released for service, compliance with this Airworthiness Directive shall be noted in the Aircraft's Records.
D. The Responsible propeller repair station will notify the Federal Aviation Administration, Chief, Engineering and Manufacturing Branch, AGL-210, 2300 East Devon Avenue, Des Plaines, Illinois 60018, by certified mail of the results of these inspections. The disposition of the affected propeller(s) including the blade and hub serial numbers of the propellers (as received and where applicable, as returned to service) must be reported. (Reporting approved by the Office of Management and Budget under OMB No. 04-R-174.)
The manufacturer's specifications and procedures identified in this directive are incorporated herein and made part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by the directive who have not already received these documents from the manufacturer, may obtain copies upon request to McCauley Accessory Division, Cessna Aircraft Corporation, Box 7, Roosevelt Station, Dayton, Ohio 45417. These documents may also be examined at the Great Lakes Regional Office, 2300 East Devon Avenue, Des Plaines, Illinois 60018, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. A historical file on this airworthiness directive which includes incorporated material in full is maintained by the FAA at its Headquarters in Washington, D.C. and the Great Lakes Region.
This amendment becomes effective: July 6, 1977.
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2004-12-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and A300 B4 series airplanes, that requires modification of the 107VU electronics rack in the avionics compartment to ensure that fluid does not enter the rack. This action is necessary to prevent the loss of electrical power during flight, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
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2021-25-04: The FAA is adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd. & Co KG (RRD) Trent 1000 model turbofan engines. This AD was prompted by the manufacturer revising the engine Time Limits Manual (TLM) life limits of certain critical rotating parts and direct accumulation counting (DAC) data files. This AD requires the operator to revise the airworthiness limitations section (ALS) of their existing approved aircraft maintenance program (AMP) by incorporating the revised tasks of the applicable TLM for each affected model turbofan engine, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
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69-06-05: 69-06-05 FAIRCHILD-HILLER: Amdt. 39-737. Applies to F-27 and FH-227 Type Airplanes Incorporating Lear Siegler (Jack & Heintz) Inverters P/N F35-5 or P/N F45-10 or P/N 40045-000 with Solid State Regulators Lear Siegler Kit P/N 52-000054 (Regulator P/N 51502-000), or Kit P/N 52-000059 (Regulator P/N 51502-001), or Kit P/N 52-000068 (Regulator P/N 51502-00M), or Bendix Type 4B39 Series Regulators.
Compliance required within the next 1200 hours time in service after the effective date of this AD unless already accomplished.
To prevent hazards associated with an inverter overvoltage condition causing the burnout or erratic operation of required instruments, accomplish the following:
(a) Install a.c. overvoltage protection in the electrical output of the above inverter(s) which utilize Lear Siegler solid state regulators, P/N 51502-000, or P/N 51502-001, or P/N 51502-00M, in accordance with Lear Siegler Service Bulletin No. 148-1 dated February 7, 1969, or F-27 aircraftand FH-227 aircraft or later FAA approved revision approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, or equivalent installation approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region.
(b) Install a.c. overvoltage protection in the electrical output of the above inverter(s) which utilize Bendix 4B39 Series regulators in accordance with Bendix Service Bulletin No. R220 dated November 15, 1968, or later FAA-approved revision approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, or equivalent installation, approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region.
(c) Upon request with substantiating data, submitted through an FAA maintenance inspector, the compliance time specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region.
This amendment is effective April 15, 1969.
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90-23-19: 90-23-19 PRATT & WHITNEY: Amendment 39-6753. Docket No. 90-ANE-11.
Applicability: Pratt & Whitney (PW) JT9D-3A/-7/-7A/-7A(SP)/-7AH/-7F/-7H/-7J/-20/-20J/-7R4D/-7R4D1/ -7R4E/-7R4E1/-7R4E4/-7R4H1/-7R4G2 turbofan engines installed on, but not limited to, Boeing 767, Boeing 747, McDonnell Douglas DC10-40, Airbus A300 and Airbus A310 aircraft.
Compliance: Required as indicated, unless already accomplished.
To prevent failure of the high pressure turbine HPT) stage one rotating air seal, which could result in an uncontained engine failure, accomplish the following:
(a) For JT9D-7R4E1 (AI 600 Series)/E4/H1 model engines, remove from service HPT stage one rotating air seal, Part Numbers (P/N) 797576, 797576P48, 793707 and 793707P48, within 60 days from the effective date of this AD, in accordance with Service Bulletin (SB) JT9D-7R4-72-392, Revision 2, dated March 2, 1990.
(b) For JT9D-7R4G2 model engines, remove from service HPT stage one rotating air seal, P/N's 797576, 797576P48, 793707 and 793707P48, at the next engine shop visit or within 2,350 cycles in service (CIS) from the effective date of this AD, whichever occurs first, in accordance with SB JT9D-7R4-72-392, Revision 2, dated March 2, 1990.
(c) For JT9D-7R4D/D1/E/E1(AI 500 Series) model engines, remove from service HPT stage one rotating air seal, P/N's 797576, 797576P48 and 793707, whose part serial numbers (S/N) are listed in Tables 1-3 inclusive of JT9D SB JT9D-7R4-72-393, Revision 1, dated December 21, 1989, at the next engine shop visit or within 2,450 CIS from the effective date of this AD, whichever occurs first, in accordance with the above noted SB.
(d) For JT9D-7R4D/D1/E/E1(AI 500 series) model engines, fluorescent penetrant inspect (FPI) HPT stage one rotating air seal, P/N's 797576, 797576P48 and 793707, whose part S/N's are not listed in Tables 1-3 inclusive of SB JT9D-7R4-72-393, Revision 1, dated December 21, 1989, in accordance with the Accomplishment Instructions, Part B, of the above noted SB, at the next HPT module exposure or within 2,900 CIS after the effective date of this AD, whichever occurs first. Remove from service parts found cracked and replace with a serviceable air seal. Thereafter, reinspect at each HPT module exposure not to exceed 2,900 cycles since last inspection (CSLI), in accordance with the above noted SB.
(e) For JT9D-3A/-7/-7A/-7A(SP)/-7AH/-7F/-7H/-7J/-20/-20J model engines, remove from service HPT stage one rotating air seals, P/N's 797576, 797576P48 and 793707, whose part S/N's are listed in Tables 1-3 inclusive of SB 5873, Revision 1, dated December 21, 1989, at the next engine shop visit or within 2,450 CIS after the effective date of this AD, whichever occurs first.
(f) For JT9D-3A/-7/-7A/-7A(SP)/-7AH/-7F/-7H/-7J/-20/-20J model engines, FPI HPT stage one rotating air seal, P/N's 797576, 797576P48 and 793707, whose part S/N's are not listed in Tables 1-3 inclusive of PW SB 5873, Revision 1, dated December 21, 1989,in accordance with the Accomplishment Instructions, Part B, of the above noted SB, at the next HPT module exposure or within 2,900 CIS from the effective date of this AD, whichever occurs first. Remove from service parts found cracked and replace with a serviceable air seal. Thereafter, reinspect at each HPT module exposure not to exceed 2,900 CSLI, in accordance with the above noted SB.
(g) For the purpose of this AD, an engine shop visit is defined as the induction of an engine into a shop for the conduct of engine maintenance.
(h) For the purpose of this AD, HPT module exposure is defined as separation of the M Flange.
(i) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished.
(j) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, an alternate method of compliance with the requirements of this AD or adjustments to the compliance schedule specifiedin this AD may be approved by the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803.
The removal and inspection procedures shall be done in accordance with the following PW documents:
Document
Page No.
Revision
Date
SB JT9D-7R4-72-392
2
Original
Oct. 25, 1989
5, 6, 8,
Rev.1
Dec. 21, 1989
9, 10
1, 3, 4, 7
Rev.2
March 2, 1990
SB JT9D-7R4-72-393
2-4
Original
Oct. 27, 1989
1, 5 thru 15
Rev. 1
Dec. 21, 1989
SB 5873
2 thru 5
Original
Oct. 30, 1989
1, 6, thru 16
Rev. 1
Dec. 20, 1989
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 Pratt & Whitney, Publications Department, P.O. Box 611, Middletown, Connecticut 06457. Copies may be inspected at the Regional Rules Docket, Office of the Assistant Chief Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Room 311, Burlington, Massachusetts 01803, or at the Office of the Federal Register, 1100 L Street NW, Room 8301, Washington, D.C. 20591.
This amendment (39-6753, AD 90-23-19) becomes effective on November 23, 1990.
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2004-11-13: The FAA is superseding an existing airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. That AD currently requires a one-time general visual inspection to determine the part number and serial number of both main landing gear (MLG) sliding tubes, and related investigative and corrective actions if necessary. This amendment adds an additional inspection to determine only the serial number of the MLG sliding tubes. This AD is prompted by a report that the field of MLG sliding tubes subject to the identified unsafe condition has expanded. We are issuing this AD to detect and correct cracking in an MLG sliding tube, which could result in failure of the sliding tube, loss of one axle, and consequent reduced controllability of the airplane.
DATES: Effective June 23, 2004.
The incorporation by reference of Airbus All Operators Telex A320- 32A1273, Revision 01, dated May 6, 2004, listed in the AD is approved by the Director of the Federal Register as of June 23, 2004.
On April 14, 2004 (69 FR 16475, March 30, 2004), the Director of the Federal Register approved the incorporation by reference of Airbus All Operators Telex A320-32A1273, dated February 5, 2004.
We must receive any comments on this AD by August 9, 2004.
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