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77-10-05: 77-10-05 BELL: Amendment 39-2893 as amended by Amendment 39-2988. Applies to Bell Model 212 helicopter certificated in all categories.
Compliance required as indicated.
To detect possible chordwise cracks in the main rotor blade skin from near the inboard end to near the outboard end and to detect eroded scarf joint filler, accomplish the following:
(a) Before the first flight of each day, after the effective date of this Airworthiness Directive, accomplish the following:
(1) Check the leading edge scarf joints of both main rotor blades for filler erosion.
(2) Clean and fill scarf joints having filler eroded to the metal, as specified in item 4 of Bell Helicopter Textron Service Bulletin No. 212-77-2 dated January 28, 1977, or later approved revision.
(3) Main rotor blades, P/N 204-012-001-33, and blades, P/N 204-012-001- 23 and -29, having serial numbers listed in Bell Service Bulletin No. 212-77-2 have an internal barrier behind the scarf joint anddo not require the check in paragraph (a)(1) of this AD. Main rotor blades, P/N 204-012-001-23 and -29 that have external cover, P/N 204-015-011-1 or -701, installed in accordance with Bell Helicopter Textron Technical Bulletin No. 212-77-6 dated April 6, 1977, or later approved revision do not require the check in paragraph (a)(1) of this AD.
(b) For all Bell Model 212 helicopters having main rotor blades with 400 or more hours' total time in service on or after the effective date of this AD, accomplish either (1) or (2) of the following after the effective date of this AD:
(1) For main rotor blades not equipped with Blade Inspection System (BIS) or not equipped with a properly functioning BIS:
(i) Inspect the complete top and bottom surfaces of each main rotor blade before the first flight of each day and at intervals not to exceed 4 hours' time in service from the last inspection as specified in Part I, paragraph A, Bell Helicopter Textron Service Bulletin No. 212-75-6, Revision B, dated May 5, 1976, or later approved revisions.
(ii) Further flight is prohibited if a crack is found in the blade skin.
(2) For main rotor blades equipped with a properly functioning BIS that was factory installed, Blade P/N 212-012-001-33, or that was installed in accordance with the procedures and requirements of Bell Service Instruction No. 212-61, 204-32, or 205-45 dated August 13, 1976, or later approved revision:
(i) Check the blade inspection system by pressing the test button on the BIS detector located on the butt end of each blade before the first flight of each day and at intervals not to exceed 4 hours' time in service from the last check.
(ii) Further flight is prohibited if a steady light on the BIS detector occurs or if a crack in the blade is confirmed.
(iii) The affected main rotor blade may be returned to service after a visual inspection is conducted in which no cracks are found and after a flashing light occurs onthe detector. (A flashing light indicates a closed or satisfactory circuit in the blade inspection system.)
(c) The checks in paragraph (a)(1) and (b)(2)(i) of this AD may be performed by the pilot.
Note: For the requirements regarding recording of compliance and method of compliance with this AD in the aircraft permanent maintenance record see FAR 91.173.
(d) Equivalent means of compliance with this AD may be approved by the Chief, Engineering and Manufacturing Branch, FAA, Southwest Region.
(e) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA, Southwest Region, may adjust the repetitive inspection intervals specified in paragraph (a) and (b) of this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator.
(f) The manufacturer's service bulletin and instruction 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 the Service Manager, Bell Helicopter Textron, P.O. Box 482, Fort Worth, Texas 76101. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 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 Southwest Regional Office in Fort Worth, Texas.
(g) Within 300 hours' blade time in service, after August 31, 1977, and before using the BIS noted in paragraph (b)(2) of this AD, modify BIS installations on all main rotor blades, P/N 204-012-001-23 and -29, and blades P/N 204-012-001-33, S/N's A2-04012, A2-04037 through A2-04042, A2-04045, A2-04046, A2-04134 through A2-04138, A2-04347, A2-04359, A2-04387, A2-04389, A2-04397, A2-04398, A2-04404 through A2-04411, A2-04455, A2- 04457, AMR-04001 through AMR-04011, AMR-04013 through AMR-04015, AMR-04017 through AMR-04020, AMR-04023, AMR-04026, AMR-04030, and AMR-54001 through AMR- 54011 to comply with Revision 2 of Bell Service Instruction No. 212-61, 204-32, or 205-45, revision of March 28, 1977, or later approved revision.
NOTE: Bell Service Bulletin No. 212-77-10 lists these blades and serial numbers.
(h) This AD does not apply to Model 212 helicopters equipped with main rotor blades having P/N 212-015-501.
Amendment 39-2893 became effective June 12, 1977.
This amendment 39-2988 becomes effective August 31, 1977.
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92-16-04: 92-16-04 AEROSPATIALE: Amendment 39-8313. Docket No. 92-NM-17-AD. Supersedes AD 89-25-12, Amendment 39-6414.
Applicability: Model ATR42 series airplanes, certificated in any category.
Compliance: Required prior to the accumulation of 10,000 landings, or within the next 300 landings after January 12, 1990 (the effective date of AD 89-25-12, amendment 39-6414), whichever occurs later, unless accomplished previously.
To prevent failure of the structural components of the fuselage and wing, accomplish the following:
(a) For airplane Serial Numbers 003 through 151, inclusive: Reinforce fuselage frame 26 in accordance with Aerospatiale Service Bulletin ATR42-53-0042, dated May 3, 1989; or Revision 1, dated April 22, 1991.
(b) For airplane Serial Numbers 003 through 032, inclusive; 034; and 035: Reinforce the fuselage secondary frames in accordance with Aerospatiale Service Bulletin ATR42-53-0023, Revision 2, dated May 25, 1989.
(c) For airplane Serial Numbers003 through 059, inclusive: Perform a cold expansion of the outer wing lower skin attach fastener holes in accordance with Aerospatiale Service Bulletin ATR42-57-0010, Revision 1, dated May 20, 1989; or Revision 2, dated April 15, 1991.
(d) For airplane Serial Numbers 003 through 071, inclusive: Reinforce fuselage frames 24 and 28 in accordance with Aerospatiale Service Bulletin ATR42-53-0004, Revision 4, dated July 25, 1989.
(e) For airplane Serial Numbers 003 through 084, inclusive; 086; 087; and 089 through 093, inclusive: Perform a cold expansion of attach holes and reinforce wing/fuselage junction fittings in accordance with Aerospatiale Service Bulletin ATR42-53-0031, Revision 1, dated May 20, 1989; or Revision 2, dated May 31, 1990; or Revision 3, dated February 19, 1991.
(f) For airplane Serial Numbers 003 through 119, inclusive: Perform a cold expansion of the wing front and rear spar attach holes in accordance with Aerospatiale Service Bulletin ATR42-57-0021,Revision 1, dated May 20, 1989; or Revision 2, dated September 25, 1990; or Revision 3, dated April 10, 1991; or Revision 4, dated August 28, 1991.
(g) For airplane Serial Numbers 003 through 151, inclusive: Replace the wing center box, in accordance with Aerospatiale Service Bulletin ATR42-57-0027, Revision 2, dated July 6, 1989; or Revision 3, dated March 27, 1991; or Revision 4, dated August 23, 1991; or Revision 5, dated October 22, 1991.
(h) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113.
NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from Standardization Branch, ANM-113.
(i) 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.
(j) The reinforcement, replacement, and the cold expansion shall be done in accordance with the following Aerospatiale service bulletins, which contain the specified effective pages:
Service Bulletin
Referenced and Date
Page Number
Revision Level
Shown on Page
Date
Shown on Page
ATR42-53-0042,
May 3, 1989
1-42
Original
May 3, 1989
ATR42-53-0042,
Revision 1,
April 22, 1991
3-40, 42
1-2, 41
Original
1
May 3, 1989
April 22, 1991
ATR42-53-0023,
Revision 2,
May 25, 1989
3-8, 10-26,
28-50, 52-53,
55-64, 66-78,
81-200, 203
2, 9, 27, 51,
54
1, 65, 79-80,
201-202
Original
1
2
July 26, 1988
January 26, 1989
May 25, 1989
ATR42-57-0010,
Revision 1,
May 20, 1989
2-5, 14,
20-381, 6-13,
15-19, 39-40
Original
1
April 18, 1989
May 20, 1989
ATR42-57-0010,
Revision 2,
April 15, 1991
5, 14, 21-38
6-13, 15,
17-19
1-4, 16, 20,
39, 40
Original
1
2
April 18, 1989
May 20, 1989
April 15, 1991
ATR42-53-0004,
Revision 4,
July 25, 1989
3-8, 13-20,
25-30, 33-34
2, 11
9, 12, 21-22,
31-32, 35-36
1, 10, 23-24,
37
Original
2
3
4
September 2, 1988
February 16, 1989
May 25, 1989
July 25, 1989
ATR42-53-0031,
Revision 1,
May 20, 1989
2-7, 10-29
1, 8-9
Original
1
January 13, 1989
May 20, 1989
ATR42-53-0031,
Revision 2,
May 31, 1990
15-17, 19-28,
1-14, 18, 29
Original
2
January 13, 1989
May 31, 1990
ATR42-53-0031,
Revision 3,
February 19, 1991
15-16, 17,
19-28
3-14, 18, 29
1-2, 15-16 bis
Original
2
3
January 13, 1989
May 31, 1990
February 19, 1991
ATR42-57-0021,
Revision 1,
May 20, 1989
3-6, 11-21
1-2, 7-10
Original
1
April 18, 1989
May 20, 1989
ATR42-57-0021,
Revision 2,
September 25, 1990
1-23
2
September 25, 1990
ATR42-57-0021,
Revision 3,
April 10, 1991
2, 4, 7-10,
12-22
1, 3, 5-6,
11, 23
2
3
September 25, 1990
April 10, 1991
ATR42-57-0021,
Revision 4,
August 28, 1991
7-9, 13-22
2-6, 11-12, 23
1, 10
2
3
4
September 25, 1990
April 10, 1991
August 28, 1991
ATR42-57-0027,
Revision 2,
July 6, 1989
5-6, 9, 11
13, 27-71
2-4, 7-8, 10,
12, 14-18,
26
1, 19-25,
72-80
Original
1
2
April 18, 1989
May 25, 1989
July 6, 1989
ATR42-57-0027,
Revision 3,
March 27, 1991
5-6, 9, 11,
13, 27-71
2-4, 7-8, 10,
12, 14-18,
26
19-25, 72-74,
76, 78, 80
1, 75, 77, 79
Original
1
2
3
April 18, 1989
May 25, 1989
July 6, 1989
March 27, 1991
ATR42-57-0027,
Revision 4,
August 23, 1991
6, 9, 11, 13,
27-71
3-4, 8, 10,
12, 14-18,
26
22-25, 72-74,
76, 78
75, 77, 79
1-2, 5, 7,
19-21
Original
1
2
3
4
April 18, 1989
May 25, 1989
July 6, 1989
March 27, 1991
August 23, 1991
ATR42-57-0027,
Revision 5,
October 22, 1991
6, 9, 11, 13,
27-71
3-4, 8, 10,
12, 14-18
22-25, 72-74
75-79
7, 19-21, 80
1-2, 5, 26
Original
1
2
3
4
5
April 18, 1989
May 25, 1989
July 6, 1989
March 27, 1991
August 23, 1991
October 22, 1991
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 Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
(k) This amendment becomes effective on October 21, 1992.
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