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71-08-04: 71-08-04 BRITISH AIRCRAFT CORPORATION: Amdt. 39-1191. Applies to Vickers Viscount Models 744, 745D, and 810 series airplanes.
Compliance is required as indicated.
To prevent a hazardous drift in the bus-bar undervoltage sensing unit setting, within the next 1000 hours' time in service after the effective date of this AD or upon installation of the bus- bar undervoltage warning light in accordance with AD 70-02-04, whichever occurs later, incorporate Rotax Modification SP7174 by replacing the transistor T.1 in the Rotax Voltage Sensing Unit Type U.3619 with a new transistor in accordance with Rotax Service Bulletin No. 24- 368 dated 4 May 1970, or later ARB-approved issue or an FAA approved equivalent.
(British Aircraft Corporation Bulletin for Modification No. D3246, 3rd Issue, dated 12 May 1970, and Bulletin for Modification FG.2123, 3rd Issue, dated 12 May 1970 refer to this subject).
This amendment becomes effective May 8, 1971.
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2016-10-09: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 and 787-9 airplanes equipped with General Electric engines. This AD was prompted by reports of cracking in barrel nuts on a forward engine mount of Model 747-8 airplanes, which shares a similar design to the forward engine mount of Model 787- 8 and 787-9 airplanes. This AD requires, for certain airplanes, replacement of the four barrel nuts of the forward engine mount on each engine. For certain other airplanes, this AD requires an inspection to determine if any forward engine mount barrel nut having a certain part number is installed; and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct cracking of the forward engine mount barrel nuts. Such cracking could result in reduced load capacity of the forward engine mount and could result in separation of an engine from the airplane and consequent loss of control of the airplane.
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77-02-04: 77-02-04 BEECH: Amendment 39-2813 as amended by Amendment 39-2842. Applies to the following Beech Models and Serial Numbers of airplanes if equipped with wing tip strobe lights, except those airplanes having Grimes Manufacturing Company (Grimes) P/Ns 30-1467-1, 30-1467-3, 30-1467-5, 30-0467-5, 30-0531-1 or 30-0692-1, Symbolic Displays P/Ns 701148-7-2, 30-0002, 30-0005, 30-0005A, 30-0005-1, 701303, 30-0218-1, 30-0218-2, 30-0020, or 30-0028, and Whelen Engineering Company P/Ns A429, A429PR, A429PG, A430, A450, A460, A460A, or A500 wing tip strobe lights installed.
MODELS
SERIAL NUMBERS
E55 and E55A
TE-768 thru TE-903
A56TC
TG-84 thru TG-94
58 and 58A
TH-1 thru TH-302
60 and 60A
P-3 thru P-222
65-B80
LD-270 thru LD-480
70
LB-1 thru LB-35
B90 and C90
LJ-318 thru LJ-502
E90
LW-1
95-B55 and 95-B55A
TC-1299 thru TC-1525
100 and A100
B-1 thru B-157
Compliance: Required as indicated, unless already accomplished.
To preclude wing tip explosion, within thenext 100 hours' time in service after the effective date of this AD, accomplish the following:
1. Visually inspect the wing tip strobe lights to determine whether Grimes P/N 30-0669-1 or Hoskins P/N 30-0187-21 strobe lights or any other strobe lights other than those excepted above are installed.
2. On those airplanes having non-explosion proof strobe lights such as Grimes Manufacturing Co. P/N 30-0669-1, Hoskins P/N 30-0187-21 or strobe lights other than those excepted by this AD, deactivate the strobe light system by installing a guard over the switch, by pulling and blocking the circuit breaker so that it cannot be inadvertently reset, or by any other suitable means.
3. Systems having Grimes Manufacturing Co. P/N 30-0669-1 or Hoskins P/N 30-0187-21 strobe lights, may be reactivated upon the installation of either Grimes Manufacturing Company P/N 30-1467-1 explosion proof strobe lights in accordance with Beechcraft Service Instructions 0800-362 or later approved revisions, or upon the installation of any explosion proof strobe lights excepted by this AD.
4. Do not reactivate strobe light installations, other than those modified per Paragraph 3, until data showing that the strobe lights are explosion proof have been submitted to and approved by the Chief, Engineering and Manufacturing Branch or Division of the FAA Region issuing the original strobe light approval.
5. Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region.
Amendment 39-2813 became effective February 24, 1977.
This amendment 39-2842 becomes effective March 3, 1977.
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2009-10-04: We are adopting a new airworthiness directive (AD) for the products listed above to supersede an existing AD. 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 case was reported where the NLG leg of a DA 40 aircraft failed in the area of the nose gear leg pivot axle. The affected airplane was mostly operated on grass runways and used for training operations. The investigation showed that the failure was due to a fatigue crack that had developed in the pivot axle. Subsequent material inspections determined that these cracks may also develop on other aircraft, depending on the type of operation.
This condition, if not detected and corrected, could lead to further cases of NLG failure, possibly causing damage to the aircraft and injuries to occupants. To address and correct this unsafecondition, ACG issued AD A-2005-005 to require repetitive inspections of the NLG leg and, in case cracks are found, replacement of the NLG leg with a serviceable unit. Since that AD was issued, Diamond Aircraft Industries developed a redesigned NLG leg which is not affected by the cracking phenomenon addressed by AD A-2005-005.
We are issuing this AD to require actions to correct the unsafe condition on these products.
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2003-18-08: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A310 series airplanes, that requires electrical conductivity testing to verify the correct heat treatment of the two half fittings holding the ejection jack for the ram air turbine (RAT). This action is necessary to prevent decreased structural integrity of the two half fittings and loss of the RAT during extension, which could lead to reduced controllability of the airplane in the event of a dual engine failure, or in the event of loss of two or all hydraulic systems. This action is intended to address the identified unsafe condition.
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70-23-03: 70-23-03\tBOEING: Amendment 39-1105 as amended by Amendment 39-1115. The following airworthiness directive, applicable to all operators of Boeing 747 airplanes is effective immediately upon receipt of telegram dated October 23, 1970. Because of three reported incidents of the pilot's or first officer's instrument panel assemblies sliding aft and producing control column interference, one of the following alternate actions is to be accomplished within 25 flight hours in service after receipt of this telegram: \n\t(1)\tInstall placard on captain and first officer instrument panel stating "Check panel security before take-off." Or \n\t(2)\tIncorporate a check item in flight crew aircraft acceptance check list stating "Check security of captain and first officer instrument panels." Or \n\t(3)\tIn the maintenance program include security of captain and first officer instrument panel as a "required inspection item" whenever the panels are disturbed, subject to the approval of the assigned principal inspector. \n\tEquivalent methods of compliance must be referred to the Chief, Aircraft Engineering Division, FAA Western Region. \n\tAs an alternative action to (1), (2), or (3), secondary safety latches may be installed in accordance with Boeing Service Bulletin 31-2005, dated November 13, 1970, or later FAA approved revision. Accomplishment of this modification will constitute of itself compliance with this AD. \n\tAmendment 39-1105 became effective upon publication in the Federal Register for all person except those to whom it was made effective immediately by telegram dated October 23, 1970. \n\tThis amendment 39-1115 becomes effective December 4, 1970.
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47-10-32: 47-10-32 LOCKHEED: (Was Service Note 2 of AD-763-3.) Applies Only to Model 49 Serial Numbers 2021 to 2067, Inclusive.
At each periodic inspection, examine the upper wing surface forward of the aileron beam and just outboard of Station 458 joint for the presence of buckles. If serious buckles are found the skin in that area should be replaced and gussets added. After the entire affected area (approximately 5 inches x 36 inches) has been reworked in this manner, no further periodic inspections will be required.
(LAC Service Instruction 49/SI-26 covers this same subject.)
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47-47-03: 47-47-03 PIPER: (Was Mandatory Note 7 of AD-780-3.) Applies to All PA-12S Seaplanes Equipped With Edo 89-2000 Floats.
Compliance required by January 15, 1948.
Racking loads imposed by rough water operation can result in damage to the airplane fuselage structure. The following inspection and modification, therefore, is necessary:
1. Inspect fuselage members to which the float braces are attached, particularly in the left side truss. Any parts damaged or bent shall be properly repaired or replaced.
2. Install wire pulls (Edo P/N 89-S-176) inboard at the lower end of the front and rear float struts and add the diagonal brace wires (Edo P/N 92-S-200-9) between the floats.
(Edo Service Bulletin No. 4 dated September 5, 1947, contains detailed instructions for this change.)
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2016-10-04: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of cracked antenna support channels, skin cracking underneath the number 2 very high frequency (VHF) antenna, and cracking in the frames attached to the internal support structure. This AD requires repetitive inspections to determine the condition of the skin and the internal support structure, and follow-on actions including corrective action as necessary. We are issuing this AD to detect and correct skin cracking of the fuselage. Such cracking could result in separation of the number 2 VHF antenna from the airplane and rapid depressurization of the cabin.
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47-20-08: 47-20-08 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.)
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