SAIB CE-02-38

SPECIAL

AIRWORTHINESS

INFORMATION

BULLETIN Aircraft Certification Service Washington, DC U.S. Department of Transportation Federal Aviation Administration No. CE-02-38 July 30, 2002 We post SAIBs on the internet at "av-info.faa.gov" This is information only. Recommendations are not mandatory.

Introduction This Special Airworthiness Information Bulletin (SAIB) advises you, a registered owner of Raytheon Aircraft Company Beech Models 45 (YT-34), A45 (T-34A, B-45), and D45 (T-34B) Airplanes, of a means to extend the compliance time of AD 2001-13-18.

Background Wing separation of a T-34 due to metal fatigue caused a fatal accident in 1999. The FAA issued AD 99- 12-02 to restrict flight to a maximum airspeed of 175 MPH and g limits between +2.5 and –0.0. On August 16, 2001, the FAA issued AD 2001-13-18, which superseded AD 99-12-02. This AD requires inspections of the front and rear spars per Raytheon SB 57-3329 by August 16, 2002, or within 80 hours time in service (TIS) after August 16, 2001, whichever occurs later, and must be repeated every 80 hours TIS.

The Raytheon repetitive inspection procedure uses an eddy current method that requires removal of fasteners. The FAA has been working with interested owners and modifiers to investigate structural modifications and alternative inspection procedures that would provide the same, or higher level of safety as the inspections required in the AD.

Recent Changes to AD 2001-13-18 Compliance Requirements Nogle and Black Aviation provided data to justify a front spar replacement per their STC with a new, stronger “common spar” and a 500-hour TIS repetitive rear spar fitting inspection. This was proposed as an Alternative Method of Compliance (AMOC) to AD 2001-13-18. The FAA approved their structural modification AMOC on July 10, 2002.

Aviadesign, Inc. provided data to justify an initial Raytheon inspection followed by installation of a steel strap (Saunders strap) to the wing per their STC, and repetitive Raytheon inspections every 2400 hours TIS. This also was proposed as an AMOC to AD 2001-13-18. The FAA approved their structural modification AMOC on July 24, 2002.

The T-34 Association, Inc. and the T-34 Technical Committee submitted a fluorescent inspection procedure to inspect for cracks in the rear spar wing attachment fitting. They proposed this as a method to extend compliance of AD 2001-13-18. The FAA approved this inspection procedure as a means to detect cracks in the rear spar fitting.

2 Compliance with AD 2001-13-18 is needed by August 16, 2002 for any airplane that has flown more than 80 hours since the AD was issued. Neither of the above-mentioned AMOCs can be accomplished in time to prevent a large portion of the T-34 fleet from being grounded unless the airplanes are inspected as specified in the AD.

The FAA agrees that the AMOCs discussed above are better long-term solutions than relying on repetitive inspections. However, the FAA believes it is unacceptable to have indefinite operation without some inspections of the spars. Now that there are sound alternatives to the repetitive inspections and because a realistic schedule required to modify the entire fleet is 1-2 years, the FAA has defined a method to allow extensions to the AD compliance.

On July 24, 2002, the FAA wrote a letter to the legal docket for AD 2001-13-18 that provides an AMOC and extension to the compliance time for that AD. (AD docket No. 2000-CE-09-AD; Amendment 39- 12300: AD 2001-13-18.)

In order to use this AMOC, the following provisions must be accomplished:

/Ga7 The operational limitations specified in paragraphs (d)(1) through (d)(3) of AD 2001-13-18 remain in effect until the airplane has been modified by an approved structural AMOC. (Maximum airspeed of 175 MPH, g limits between –0.0 and +2.5, and no acrobatic maneuvers.)

/Ga7 Within the next 20 hours TIS after August 1, 2002, accomplish the rear spar attach fitting inspection per the instructions of T-34 Technical Committee Report No. 071102 Part 1, Rev. IR, Appendix A, dated July 11, 2002. If cracks are found, no further flight is permitted until both the front spar and rear spar fitting are repaired or replaced. The owner must notify the FAA (Wichita Aircraft Certification Office) immediately if cracks are found.

/Ga7 Repeat the rear spar fitting inspection within the next 100 hours TIS. This provides an additional 100 hours TIS, for a total of 200 hours TIS after the initial inspection.

/Ga7 Owners retain proof that they are scheduled for completion of an approved structural AMOC. This will include the name of the modifier and scheduled date of modification.

/Ga7 The structural AMOC modification must be accomplished within 24 months or 200 hours TIS after the first rear spar fitting inspection, whichever occurs first.

/Ga7 Owners must provide rear spar fitting inspection results to the modifier the owner has selected for the structural AMOC. The modifier will maintain this information for all airplanes scheduled for that form of modification and will provide the inspection results to the FAA monthly.

/Ga7 Modifiers holding approved AMOCs to the AD must share with the FAA their schedule of modifications and records of modifications completed.

The FAA will review the rear spar fitting inspection results and monitor the progress of each modifier’s schedules. If rear spar fitting inspections indicate adverse trends, or if modifiers or owners are not holding to completion schedules, regulatory action will be initiated.

The FAA will revise this SAIB if additional AMOCs are approved.

3 Recommendation If your T-34 is approaching 80 hours TIS since August 16, 2001, you may consider modifying your wings according to an FAA approved AMOC. In order to extend operation beyond the limits of AD-2001-13- 18, you will need to comply with the extension provisions described above.

You can obtain the necessary rear spar fitting inspection procedures from the T-34 Technical Committee.

Their contact information is at the end of this Bulletin.

In order to show proof that you are complying with the requirements of the compliance extension, the initial and repeat inspection results must be recorded in your airplane’s maintenance logs. You should also provide these results to the modifier you have chosen to complete an approved modification AMOC.

You will also need to retain proof that you are scheduled for completion of an approved modification AMOC. Once you have committed to a modification, the approved modifier will issue you a letter stating that you are scheduled for the modification and the estimated completion date. This letter will serve as proof of your intent. In order to show compliance with the provisions of the AMOC, you should also retain a copy of this letter with your maintenance records. This information will then be available to your local authorized inspector (IA) or FAA inspector.

You must have your airplane modified within 24 months or within the next 220 hours TIS to avoid noncompliance with the AD. When your airplane has been modified, routine maintenance logbook entries will document your compliance with the AD and AMOC. The flight operation limitations of AD 2001- 13-18 will be removed at that time.

The FAA will monitor the rear spar fitting inspection results to verify that no immediate fleet safety issues exist. The FAA will also monitor the progress of the modifications to verify that the modifiers and owners are working to complete their modifications according to their schedules and in a timely manner.

For Further Information Contact:

T-34 Association, Inc. Copies of the rear spar fitting fluorescent penetrant inspection procedure may be obtained by contacting the T-34 Association, Inc., and the Technical Committee. Their contacts are: Tim Roehl or George Braly, General Aviation Modifications, Inc. (GAMI), 2800 Airport Rd. Hangar A, Ada, OK 74820; telephone: (580) 436-4833; Fax: (580) 436-6622; E-mail: troehl@gami.com, or gwbraly@gami.com FAA, Wichita Aircraft Certification Office, Attention Paul Nguyen, ACE 118W, 1801 Airport Road, Room 100, Wichita, KS 67209; telephone: (316) 946-4125; fax: (316) 946-44407; E-mail:

paul.nguyen@faa.gov FAA, Small Airplane Directorate, Attention Marv Nuss, ACE-113, 901 Locust, Room 301, Kansas City, MO 64106; telephone: (816) 329-4117; fax: (816) 329-4090; E-mail: marvin.nuss@faa.gov