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2010-18-04: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:
It has been found the possibility of cracks developing in the ram air turbine (RAT) machined support, located in the forward compartment [zone 124] of [the] aircraft, due to downlock pin not [being] pull[ed] during its retraction. In case of RAT failure or malfunction, it will not provide electrical power to essential systems of [the] aircraft in [an] electrical emergency situation.
* * * * *
Lack of electrical power could result in reduced controllability of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
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96-13-08: 96-13-08 PRATT & WHITNEY: Amendment 39-9676. Docket 96-ANE-10.
Applicability: Pratt & Whitney (PW) PW4000 series turbofan engines, with thrust reverser, Supplemental Type Certificate (STC) No. SJ514NE, installed on Airbus A300-600 and A310 series aircraft, and thrust reverser, STC No. SE744NE, installed on McDonnell Douglas MD-11 series aircraft. These thrust reversers incorporate aft cascade support frame assemblies, Part Numbers (P/N's) 221-0516-503 and 221-0516-504. NOTE: This airworthiness directive (AD) applies to each engine with affected thrust reversers 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 with affected thrust reversers 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 (c) 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 with affected thrust reversers from the applicability of this AD.
Compliance: Required as indicated, unless accomplished previously.
To prevent aft cascade support frame assembly failure due to cracks, which can result in thrust reverser hardware liberation and ejection from the aircraft during thrust reverser operation, which can contaminate the runway with debris, causing an operational hazard to other aircraft during takeoff and landing, accomplish the following:
(a) For engines with affected thrust reversers installed on Airbus A300-600 and A310 series aircraft, accomplish the following:
(1) Initially inspect aft cascade support frame assemblies for cracks within 250 flight hours after the effective date of this AD, in accordance with the Accomplishment Instructions, Part 1 -- Interim Inspection, of PW Service Bulletin (SB) No. PW4NAC 78-78, Revision 6, dated March 6, 1996.
(2) Thereafter, inspect aft cascade support frame assemblies for cracks at intervals not to exceed 450 flight hours since the last inspection, in accordance with the Accomplishment Instructions, Part 1 -- Interim Inspection, of PW SB No. PW4NAC 78-78, Revision 6, dated March 6, 1996.
(3) For aft cascade support frame assemblies that do not meet the return to service criteria stated in the Accomplishment Instructions, Part 1 -- Interim Inspection, of PW SB No. PW4NAC 78-78, Revision 6, dated March 6, 1996, prior to further flight, accomplish either of the following:
(i) Remove from service cracked aft cascade support frame assemblies, and replace with a serviceable part; or
(ii) Lockout the thrust reverser in accordance with the Airbus A300- 600 and A310 series Aircraft Maintenance Manuals, as applicable, for a time period not to exceed 10 days. At the conclusion of the 10-day lockout period, prior to further flight remove any cracked aft cascade support frame assemblies and replace with serviceable parts.
(b) For engines with affected thrust reversers installed on McDonnell Douglas MD- 11 series aircraft, accomplish the following:
(1) Initially inspect aft cascade support frame assemblies for cracks within 250 flight hours after the effective date of this AD, in accordance with the Accomplishment Instructions, Part 1 -- Interim Inspection, of PW SB No. PW4MD11 78-67, Revision 5, dated March 6, 1996.
(2) Thereafter, inspect aft cascade support frame assemblies for cracks at intervals not to exceed 450 flight hours since the last inspection, in accordance with the Accomplishment Instructions, Part 1 -- Interim Inspection, of PW SB No. PW4MD11 78-67, Revision 5, dated March 6, 1996.
(3) For aft cascade support frame assemblies that do not meet the return to service criteria stated in the Accomplishment Instructions, Part 1 -- Interim Inspection, of PW SB No. PW4MD11 78-67, Revision 5, dated March 6, 1996, prior to further flight, accomplish either of the following:
(i) Remove from service cracked aft cascade support frame assemblies, and replace with a serviceable part; or
(ii) Lockout the thrust reverser in accordance with the McDonnell Douglas MD-11 series Aircraft Maintenance Manual, for a time period not to exceed 10 days. At the conclusion of the 10-day lockout period, prior to further flight remove any cracked aft cascade support frame assemblies and replace with serviceable parts.
(c) 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, Engine Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office.
NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office.
(d) 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.
(e) The actions required by this AD shall be done in accordance with the following PW SB's:
Document No.
Pages
Revision
Date
PW4NAC 78-78
1
6
March 6, 1996
2,3
2
October 31, 1995
4-6
6
March 6, 1996
7
5
October 31, 1995
8-11
6
March 6, 1996
12
5
October 31, 1995
13-19
6
March 6, 1996
20-22
5
October 31, 1995
23-34
6
March 6, 1996
35
5
October 31, 1995
36,37
6
March 6, 1996
38
5
October 31, 1995
39,40
6
March 6, 1996
Total pages: 40.
PW4MD11 78-67
1-38
5
March 6, 1996
Total pages: 38.
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, 400 Main St., East Hartford, CT 06108; telephone (860) 565-6600, fax (860) 565-4503. 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.
(f) This amendment becomes effective on August 1, 1996.
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2010-17-15: We are adopting a new airworthiness directive (AD) for certain Hawker Beechcraft Corporation Model 390 airplanes. This AD requires you to inspect for installation of certain serial number (S/N) starter generators and replace the starter generator if one with an affected serial number is found. This AD results from reports that starter generators with deficient armature insulating materials may have been installed on certain airplanes. We are issuing this AD to detect and replace starter generators with defective armature insulating materials. This condition could result in the loss of operation of one or both starter generators with consequent loss of all non battery electrical power.
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75-26-10: 75-26-10 SIKORSKY AIRCRAFT: Amendment 39-2461. Applies to S-61L, S-61N, and S-61NM helicopters certificated in all categories.
Compliance required as indicated.
As a result of the completion of a recent engineering evaluation program and the development of additional substantiating data, a new schedule of replacement times has been established for the components of S-61 helicopters.
(a) After the effective date of this AD, the replacement of S-61 components must be accomplished in accordance with the schedule of Section 2C of Sikorsky Service Bulletin No. 61B General-1F dated October 20, 1975, or later FAA approved revisions.
(b) 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 Sikorsky Aircraft, Stratford, Connecticut 06602. These documents may also be examined at FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, 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 the FAA, New England Region, Burlington, Massachusetts.
This supersedes Amendment 39-1167 (36 F.R. 4689), AD 71-06-02 as amended by Amendment 39-1271 (36 F.R. 16186), Amendment 39-1948 (39 F. R. 31626), and Amendment 39-1978 (39 F.R. 34649).
This amendment becomes effective January 2, 1976.
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94-13-08: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A310 and A300-600 series airplanes. This action requires inspections and replacement or reinstallation of certain aft engine mount link assemblies. This amendment is prompted by reports of cracking in the aft engine mount link assemblies. The actions specified in this AD are intended to prevent loss of the capability of the aft engine mount to support engine loads, and possible separation of the engine from the airplane.
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78-02-04: 78-02-04 HAWKER SIDDELEY AVIATION, LIMITED: Amendment 39-3130. Applies to Model BH/HS 125-600A airplanes certificated in all categories.
Compliance is required as indicated, unless already accomplished.
To prevent possible loss of airspeed reference to both the pilot and co-pilot due to failure of the heating elements of both pitot heads, within 10 hours time in service after the effective date of this AD, remove the Avimomini pitot heads (L/H and R/H) and replace with Rosemount Model 853 JA pitot heads in accordance with the section entitled "Accomplishment Instructions" and the associated installation drawing, both included in Hawker Siddeley Aviation, Limited Service Bulletin 34-129(2436), Revision 1, dated June 21, 1977, or an FAA-approved equivalent.
This amendment becomes effective February 6, 1978.
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2010-18-03: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:
Several in service events related to various electrical systems, have led to the discovery of a common root cause: A leakage failure mode of Transient Voltage Suppressor (TVS) diodes used on Power Distribution Control Units (PDCU) cards or Generator Control Unit (GCU) cards in the Primary Power Distribution Boxes (PPDB). Due to such TVS diode failure mode, operation of some electrical circuits is degraded and some control signals are set at unexpected levels. Further analysis indicated that combination of a TVS diode failure with other systems failures could significantly reduce flight safety.
* * * * *
The unsafe condition is a leakage failure mode of TVS diodes used on PDCU cards or GCU cards in the PPDB, which in combination with other system failures could lead to loss of controllability of the airplane. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
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71-06-09 R1: 71-06-09 R1 BRITISH AEROSPACE: Amendment 39-1177 as amended by Amendment 39- 4737. Applies to BAC 1-11 200 and 400 series airplanes, certificated in all categories. Compliance is required as indicated. To prevent malfunction of the auxiliary power unit (APU) air delivery duct nonreturn valve, accomplish the following:
A. For airplanes having nonreturn valve P/N 525180 installed:
1. Within the next 100 hours time in service after the effective date of this AD, unless already accomplished within the previous 60 hours time in service and thereafter at intervals not to exceed 160 hours time in service, perform the actions specified by paragraphs 2.2, 2.3, 2.4, and 2.5 of Accomplishment Instructions, British Aerospace Alert Service Bulletin 49- A-PM3122, Issue 4, dated March 31, 1982. Incorporation of British Aerospace modification PM3254 or PM4912 terminates the requirements of paragraphs 2.3 and 2.4 of the service bulletin.
2. Prior to further flight, unless alreadyaccomplished, install a placard adjacent to the APU control panel in clear view of the pilot, or amend the Airplane Flight Manual limitations Section 2, to read as follows: "Close APU air delivery valve when starting engine from an external supply or by cross-feeding air from an operating engine. Close APU air delivery valve and shut down APU for takeoff and flight operations. Operational use of the APU in flight is prohibited." The placard may be removed or the amendment to the Airplane Flight Manual may be deleted upon replacement of APU air delivery duct nonreturn valve P/N 525180 with nonreturn valve P/N 1398B000 or 1398B000/1398B999 or 3031B000.
B. For airplanes having nonreturn valve P/N 1398B000 or 1398B000/1398B999 installed, within the next 750 hours time in service after the effective date of this AD, unless already accomplished within the previous 1,500 hours time in service from the last inspection, and thereafter at intervals not to exceed those specified in the service bulletin, perform the actions described by paragraphs 2.4.1, 2.4.2, and 2.4.3 of the service bulletin.
C. Incorporation of modifications PM3148, PM3177 and PM4912 constitutes terminating action for the repetitive inspections required by this AD.
D. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region.
E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD.
Amendment 39-1177 became effective April 16, 1971.
This Amendment 39-4737 becomes effective November 3, 1983.
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84-19-51 R1: 84-19-51 R1 SIKORSKY AIRCRAFT: Amendment 39-5008. Applies to Model S-76A helicopters Serial Numbers 76006, 76007, 760001 through 760339 certificated in all categories.
Compliance is required prior to further flight, unless already accomplished.
To prevent operation with damaged, bent, or fractured center firewall support stiffeners or doublers which could cut into the tail rotor driveshaft and cause loss of directional control of the helicopter, accomplish the following:
(a) Inspect the forward center firewall sections for missing fasteners and proper fit, as required in paragraphs E(1) through E(5)(C) of Sikorsky Alert Service Bulletin (ASB) 76-53-25 or FAA approved equivalent.
(b) If doubler, Part Number (P/N) 76070-20057-101, is cracked or fails to conform to the firewall contour or to the limits specified in ASB 76-53-25, paragraph E(5)(B), remove and replace as per paragraph E(5)(D) or FAA approved equivalent.
(c) If the rivets are not installed as required in paragraph (a) above, comply with paragraph E(5)(E) of ASB 76-53-25 or FAA approved equivalent.
(d) Remove the core section from the horizontal seal, P/N 76304-07003-127 or 76304-07003-137, on the aft engine cowl center section fixed or adjustable firewall assembly, P/N 76304-07003-041 or 76304-07003-044, respectively.
(e) Inspect stiffeners and doublers used to support the center firewall installation for fractures, distortions, or damage. Assure that the forward edges of the removable center firewall are properly engaged in the slots.
(f) Inspect the area between the number 1 section of the tail rotor driveshaft called out in Sikorsky Maintenance Manual (MM) SA 4047-76-2, Section 66-40-00, Figure 401, and the engine compartment center firewall for clearance in accordance with section 5-50-00 of the Airworthiness and Inspection Requirement Manual. If inadequate clearance is found, contact the Boston Aircraft Certification Office (617) 273-7113 or (617) 273-7001 prior to further flight.
(g) Helicopters not modified in accordance with Sikorsky Customer Service Notice 76-111 are required to accomplish the inspection of paragraph If) of this AD only.
(h) Special flight permits may be issued in accordance with FAR Sections 21.197 and 21.199 to operate helicopters to a base for accomplishment of this AD.
(i) Alternate repairs, modifications, or other means of compliance with the AD which provide an equivalent level of safety may be approved by the Manager, Boston Aircraft Certification Office, FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803.
This amendment becomes effective March 7, 1985, as to all persons except those persons to whom it was made immediately effective by telegraphic AD's T84-19-51 issued September 27, 1984, and T84-19-51 R1 issued October 15, 1984, which contained this amendment.
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2010-17-06: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:
A PW617F-E engine powered twin engined aircraft had recently experienced an uncommanded power reduction on one of its engines. Investigation showed that the Fuel Filter Bypass Valve poppet in the Fuel Oil Heat Exchanger (FOHE) on that engine had worn through the housing seat, allowing unfiltered fuel and debris to contaminate the Fuel Metering Unit (FMU), resulting in fuel flow drop and subsequent power reduction. P&WC has confirmed that this is a dormant failure that could result in an unsafe condition.
The PW615F-A engine Fuel Filter Bypass Valve installation is very similar to that of PW617F-E, but so far there have been no operational abnormalities reported due to subject valve failure on PW615F-A engines. However, evaluation by P&WC has confirmed similar dormant failure of worn through poppets of the subject valve on some PW615F-A engine installations, which could affect both engines at the same time on an aircraft and may result in an unsafe condition. We are issuing this AD to prevent uncommanded power reduction, which could result in the inability to continue safe flight and safe landing.
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