Strut Service Bulletin

[Guest]

Re: Strut Service Bulletin

Just started to read part 11, I see AD's are listed there

[Ragwing nut]

Re: Strut Service Bulletin

Hi Mike,

Do AD's normally show up in NPRM? I am not real familiar with the process. The engineers say it in process but maybe that means its on its way to NPRM and I was not sharp enough to catch that.

Dave

Notice of Proposed Rule Making is used when changes or additions to the regulations are being made. Not sure if AD's fall directly under that umbrella, but there is a open public comment period that is suppose to be published for proposed AD's

Mike

[Guest]

Re: Strut Service Bulletin

Dave, post that info on this thread. Perhaps if enough people are on board with it, I would volunteer to draft a strongly worded petition that can be presented by the Foundation as one voice, but with 100 or 200 signatures on it.

Meantime I will draft a letter which any interested parties are free to use on an individual basis.

Bill

Bill and all,

I have only phone numbers not addresses. In my post I offered to share phone numbers. I suppose if you call it they can give you an address.

I will not publish anyone's phone number on a forum.

I would not want that done to me and therefore will not do it to anyone else.

If you want to call the FAA contact me privately if you would like the numbers that I called. I'll ask you also to refrain from posting it as I do not want to be part of that.

Dave.

[DanBrown]

Re: Strut Service Bulletin

Count me in on sending a letter and/or email using Bill's as a template. Does anyone have a name, email address or telephone # for an appropriate FAA person?

[Guest]

Re: Strut Service Bulletin

Dave,

Did the Federales tell you what item or items the second AD is going to address?? And regarding the SB, is the only approved part # in the AD that refers to struts the same part # as the SB--which would exclude Univair struts?

Frank

Hi Frank,

He indicated to me that sealed struts from other sources would also be acceptable so Univair's and whoever's will be ok. (Talking about the AD only)
AD will superscede the SB.

I suppose there would be the possibility of testing a used one and then sealing it too as an alternate method of compliance. But I did not ask that question. I like that idea though.


Dave

[astjp2]

Re: Strut Service Bulletin

Nope, it would have to be virgin metal when sealed or it will not be considered sealed. The part number changed when they went to sealed struts. Tim

[Tony Johnson]

Re: Strut Service Bulletin

I do not see the D models listed in the service bulletin. Am I missing something?

[DanBrown]

Re: Strut Service Bulletin

It includes "BC12-D, BCS12-D, BC12-D1, BCS12-D1, BC12D-85, BCS12D-85, BC12D-4-85, BCS12D-4-85". It doesn't specifically list the BF (which is still on my registration, although the log has it converted to a BC-65) and BL models, but I believe the type certificate covers all these and the postings indicate the same struts were used. It was restored in 1984 -- there is no note on what struts were used -- so I expect the SB applies to me also.

[Dick Huish]

Re: Strut Service Bulletin

The model "D" (all tandems) are covered on TC 746. The Converted gliders (TG-6) included under 746. So the Struts are not covered. Dick

[Tony Johnson]

Re: Strut Service Bulletin

Dick,

Thanks for that information. I wonder why the D models are not included in the SB? I also wonder if the anticipated AD would include the D models? It will be interesting to see the AD when and if it comes out to determine what airplanes it covers and whether or not the univair struts will be acceptable.

[tabranch]

Re: Strut Service Bulletin

Perhaps the AD should just require the replacement of all struts on any airplane the has struts? Or maybe the failure or corrosion data should be the determining factor!

[DannyDot]

Re: Strut Service Bulletin

It includes "BC12-D, BCS12-D, BC12-D1, BCS12-D1, BC12D-85, BCS12D-85, BC12D-4-85, BCS12D-4-85". It doesn't specifically list the BF (which is still on my registration, although the log has it converted to a BC-65) and BL models, but I believe the type certificate covers all these and the postings indicate the same struts were used. It was restored in 1984 -- there is no note on what struts were used -- so I expect the SB applies to me also.

I have a 1941 BL-65. I don't see it on the list, but that doesn't matter that much to me -- unless there is some reason to think BL-65 struts are "different". I am leaning strongly in the direction of new struts. My plane went for several years without flying. I have no idea if it was outside during that time frame. As far as I know the plane was outside and I have massive corrosion in the struts.

Living to be an old man is more important than weather I have to follow an SB or an AD. I just want to make sure I don't have to do the inspection every 2 years after buying new struts. I would feel better if the Univar part number was called out in the SB/AD.

I will wait for the AD to come out before I buy new struts -- just to make sure I am buying the right product.

Danny Deger

[Ragwing nut]

Re: Strut Service Bulletin

Since the factory does not hold all the TC's for taylorcrafts, it will only affect the ones they hold the TC for. However when and if an AD comes out, I would bre certain it will include all ""B" models. Depending on how smart the FAA guy is, it may even cover "D" models.

Mike

[Guest]

Re: Strut Service Bulletin

Since the factory does not hold all the TC's for taylorcrafts, it will only affect the ones they hold the TC for. However when and if an AD comes out, I would bre certain it will include all ""B" models. Depending on how smart the FAA guy is, it may even cover "D" models.

Mike

Mike I think you are right on.

I remember the FAA fellow talking about the other TC's and TC holders.

Dave

[Steve Pierce]

Re: Strut Service Bulletin

Just got an email from the FAA. The AD has been issued.

http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgAD.nsf/0/DE9AC9E836BBA6F58625733600582B05?OpenDocument

Federal Register: August 13, 2007 (Volume 72, Number 155)] [Rules and Regulations] [Page 45153-45156] From the Federal Register Online via GPO Access [wais.access.gpo.gov] [DOCID:fr13au07-4] –––––––––––––––––––––––––––––––––– DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2007-28478; Directorate Identifier 2007-CE-057-AD; Amendment 39-15153; AD 2007-16-14] RIN 2120-AA64 Airworthiness Directives; Taylorcraft A, B, and F Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. –––––––––––––––––––––––––––––––––– SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all Taylorcraft A, B, and F series airplanes. This AD requires you to initially inspect the left and right wing front and aft lift struts for corrosion and cracks, replace any cracked strut or strut with corrosion that exceeds certain limits with either sealed or non-sealed struts, and repetitively inspect any non-sealed struts. This ADresults from inspections where several different struts were found with moderate to severe corrosion and required strut replacement. We are issuing this AD to detect and correct corrosion or cracks in the right and left wing front and aft lift struts. This condition, if not corrected, could result in failure of the lift strut and lead to in-flight separation of the wing with consequent loss of control. DATES: This AD becomes effective on August 20, 2007. On August 20, 2007, the Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD. We must receive any comments on this AD by October 12, 2007. ADDRESSES: Use one of the following addresses to comment on this AD. • DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically.• Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Fax: (202) 493-2251. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.
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2 • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. To get the service information identified in this AD, contact Taylorcraft Aviation, LLC, 2124 North Central Avenue, Brownsville, Texas 78521; telephone: (956) 986-0700. To view the comments to this AD, go to http://dms.dot.gov. The docket number is FAA-2007-28478; Directorate Identifier 2007-CE-057-AD. FOR FURTHER INFORMATION CONTACT: Andrew McAnaul, Aerospace Engineer, ASW-150 (c/o MIDO-43), 10100 Reunion Place, Suite 650, San Antonio, Texas 78216; telephone: (210) 308-3365; fax: (210) 308-3370. SUPPLEMENTARY INFORMATION: Discussion The FAA has received reports of several corroded wing lift struts from different Taylorcraft series airplanes. Independent laboratory analysis of the struts revealed varying degrees of excessive internal and external corrosion, including through-the-thickness corrosion. The struts exhibited corrosion severe enough to require strut replacement. Additional Taylorcraft owners reported finding severe corrosion on wing struts during routine maintenance, which required strut replacement. These same findings confirm strut corrosion Taylorcraft reported to the FAA. The internal cavity of the original design (vented) lift struts is exposed to the external environment and can hide internal surface corrosion resulting from environmental exposure. External surface corrosion can be masked by the external paint coating. This condition, if not corrected, could result in failure of a wing lift strut due to corrosion and lead to separation of the wing from the airplane with consequent loss of control. Relevant Service Information We reviewed Taylorcraft Aviation, LLC Service Bulletin (SB) No. 2007-001, Revision A, dated August 1, 2007. The service information describes procedures for wing lift strut assembly corrosion inspection and/or replacement. FAA's Determination and Requirements of This AD We are issuing this AD because we evaluated all the information and determined the unsafe condition described previously is likely to exist or develop on other products of the same type design. This AD requires you to initially inspect the left and right wing front and aft lift struts for corrosion and cracks, replace any cracked strut or strut with corrosion that exceeds certain limits with either sealed or non-sealed struts, and repetitively inspect any non-sealed struts.The FAA is determining whether future rulemaking action is necessary. This could include inspection and/or modification or replacement in adjacent structure. In preparing this rule, we contacted type clubs and aircraft operators to get technical information and information on operational and economic impacts. We have included a discussion of information that may have influenced this action in the rulemaking docket. FAA's Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule
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3 because corrosion and/or cracks in the wing lift struts could result in separation of the wing from the airplane with consequent loss of control. Therefore, we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in fewer than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and an opportunity for public comment. We invite you to send any written relevant data, views, or arguments regarding this AD. Send your comments to an address listed under the ADDRESSES section. Include the docket number ''FAA-2007-28478; Directorate Identifier 2007-CE-057-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the AD. We will consider all comments received by the closing date and may amend the AD in light of those comments. We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive concerning this AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ''General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ''significant regulatory action'' under Executive Order 12866; (2) Is not a ''significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant economic impact, positive or negative, on a substantial number ofsmall entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. Examining the AD Docket You may examine the AD docket that contains the AD, the regulatory evaluation, any comments received, and other information on the Internet at http://dms.dot.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.
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4 The Docket Office (telephone (800) 647-5527) is located at the street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39–AIRWORTHINESS DIRECTIVES1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD):
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5 FAA Aircraft Certification ServiceAIRWORTHINESS DIRECTIVEwww.faa.gov/aircraft/safety/alerts/ www.gpoaccess.gov/fr/advanced.html2007-16-14 Taylorcraft: Amendment 39-15153; Docket No. FAA-2007-28478; Directorate Identifier 2007-CE-057-AD. Effective Date (a) This AD becomes effective on August 20, 2007. Affected ADs (b) None. Applicability(c) This AD applies to all serial numbers of Taylorcraft Models A, BC, BCS, BC-65, BCS-65, BC12-65 (Army L-2H), BCS12-65, BC12-D, BCS12-D, BC12-D1, BCS12-D1, BC12D-85, BCS12D-85, BC12D-4-85, BCS12D-4-85, (Army L-2G) BF, BFS, BF-60, BFS-60, BF-65, BFS-65, (Army L-2K) BF 12-65, BL, BLS, (Army L-2F) BL-65, BLS-65, (Army L-2J) BL12-65, BLS12-65, FA-III (Airphibian), 19, F19, F21, F21A, F21B, F22, F22A, F22B, F22C, and TG-6 Conversion airplanes that: (1) Are certificated in any category; and (2) Do not incorporate in all struts new sealed front lift struts (P/N MA-A815 or FAA-approved equivalent P/N) and new sealed aft lift struts (P/N MA-A854 or FAA-approved equivalent P/N). Note: This AD applies to all Taylorcraft models listed above, including those not listed in Taylorcraft Aviation, LLC Service Bulletin No. 2007-001, Revision A, dated August 1, 2007. If there are any other differences between this AD and the above service bulletin, this AD takes precedence. Unsafe Condition (d) This AD results from inspections where several different struts were found with moderate to severe corrosion and required strut replacement. We are issuing this AD to detect and correct corrosion or cracks in the right and left wing front and aft lift struts, which could result in failure of the lift strut and lead to in-flight separation of the wing with consequent loss of control. Compliance(e) To address this problem, you must do the following, unless already done:
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6 Actions Compliance Procedures(1) Visual Inspection: Visually inspect for corrosion or cracking in the lower 12 inches of the left and right wing front lift struts (part number (P/N) A-A815 or FAA-approved equivalent P/N) and aft lift struts (P/N A-A854 or FAA-approved equivalent P/N) and then inspect per paragraph (e)(2) of this AD. Within the next 5 hours time-in-service after August 20, 2007 (the effective date of this AD), unless the strut has: (i) been replaced with parts specified in either paragraph (e)(4)(i); or (ii) been replaced with parts specified by paragraph (e)(4)(ii) of this AD and been installed on an airplane for less than 24 months. Follow Part 1 of the Instructions in Taylorcraft Aviation, LLC Service Bulletin No. 2007-001, Revision A, dated August 1, 2007. (2) Initial Eddy Current or Ultrasound Inspection: Inspect using the eddy current or ultrasound inspection methods to detect corrosion or cracking in the lower 12 inches of the left and right wing front lift struts (P/N A-A815 or FAA-approved equivalent P/N) and aft lift struts (P/N A-A854 or FAA-approved equivalent P/N). The eddy current or ultrasound inspection must be done by one of the following: (i) A Level II or III inspector certified in the applicable eddy current or ultrasound inspection method using the guidelines established by the American Society of Nondestructive Testing or NAS 410 (formerly MIL-STD-410); (ii) An inspector certified to specific FAA or other acceptable government or industry standards, such as Air Transport Association (ATA) Specifications 105-Guidelines for Training and Qualifying Personnel in Nondestructive Testing Methods; or (iii) A qualified FAA Repair Station or a qualified Testing/Inspection Laboratory. Initially inspect any original design (vented) strut or FAA-approved equivalent part number at whichever of the following that applies; (A) Before further flight when corrosion or cracking is found during the visual inspection required in paragraph (e)(1) of this AD; or (B) If no corrosion or cracking is found during the visual inspection in paragraph (e)(1) of this AD, within the next 3 months after August 20, 2007 (the effective date of this AD) or within 24 months of installation of the strut, whichever occurs later. Follow Part 2 of the Instructions in Taylorcraft Aviation, LLC Service Bulletin No. 2007-001, Revision A, dated August 1, 2007.
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7 (3) Repetitive Eddy Current or Ultrasound Inspections:Inspect using the eddy current or ultrasound inspection methods to detect corrosion or cracking in the lower 12 inches of the left and right wing front lift struts (P/N A-A815 or FAA-approved equivalent P/N) and aft lift struts (P/N A-A854 or FAA-approved equivalent P/N). The eddy current or ultrasound inspection must be done by one of the following: (i) A Level II or III inspector certified in the applicable Eddy Current or Ultrasound Inspection method using the guidelines established by the American Society of Nondestructive Testing or NAS 410 (formerly MIL-STD-410), (ii) An Inspector certified to specific FAA or other acceptable government or industry standards, such as Air Transport Association (ATA) Specifications 105-Guidelines for Training and Qualifying Personnel in Nondestructive Testing Methods, or (iii) A qualified FAA Repair Station or a qualified Testing/Inspection Laboratory. (A) For original or replacement left and right wing front lift struts (P/N A-A815 or FAA-approved equivalent P/N) and aft lift struts (P/N A-A854 or FAA-approved equivalent P/N) of original design (vented), repetitively inspect at intervals not to exceed 24 months after the initial inspection required in paragraph (e)(2) of this AD. (B) Replacement of all struts with new sealed front lift struts (P/N MA-A815 or FAA-approved equivalent P/N) and new sealed aft lift struts (P/N MA-A854 or FAA-approved equivalent P/N) eliminates the repetitive inspection requirement of this AD. (C) If not all the vented lift struts are replaced with new sealed units, then the lift struts that are not new sealed units are still subject to the repetitive inspection requirement of this AD. Follow Part 2 of the Instructions in Taylorcraft Aviation, LLC Service Bulletin No. 2007-001, Revision A, dated August 1, 2007. (4) Replacement: Replace the original design (vented) front lift struts (P/N A-A815 or FAA-approved equivalent P/N) and original design (vented) aft lift struts (P/N A-A854 or FAA-approved equivalent P/N) with one of the following: (i) new sealed front lift struts, (P/N MA-A815 or FAA-approved equivalent P/N) and new sealed aft lift struts, (P/N MA-A854 or FAA-approved equivalent P/N); or (ii) new original design (vented) front lift struts (P/N A-815 or FAA-approved equivalent P/N) and new original design (vented) aft lift struts (P/N A-A854 or FAA-approved equivalent P/N). Replace before further flight any time cracking or corrosion is found during any required eddy current or ultrasound inspection that exceeds the acceptance/rejection criteria limits in Taylorcraft Aviation, LLC Service Bulletin No. 2007-001, Revision A, dated August 1, 2007. After replacing with an original design (vented) strut, begin the repetitive inspectionsof paragraph (e)(3) within 24 months after installation. Follow Taylorcraft Aviation, LLC Service Bulletin No. 2007-001, Revision A, dated August 1, 2007. Alternative Methods of Compliance (AMOCs) (f) The Manager, Fort Worth Airplane Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Andrew McAnaul, Aerospace Engineer, ASW-150 (c/o MIDO-43), 10100 Reunion Place,
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8 Suite 650, San Antonio, Texas 78216; telephone: (210) 308-3365; fax: (210) 308-3370. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Material Incorporated by Reference(g) You must use Taylorcraft Aviation, LLC Service Bulletin No. 2007-001, Revision A, dated August 1, 2007, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Taylorcraft Aviation, LLC, 2124 North Central Avenue, Brownsville, Texas 78521; telephone: 956-986-0700. (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_regi...locations.html. Issued in Kansas City, Missouri, on August 3, 2007. David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-15581 Filed 8-10-07; 8:45 am]