AD appears to ground T-34 fleet pending
action, follows second Texas Air Aces fatal crash
The Federal Aviation Administration has issued an Emergency AD
applicable to all T-34 aircraft, all models.
This action follows the second accident involving a
Texas Air Aces T-34 in which the instructor pilot and passenger
perished after eyewitnesses reported separation of one of the
aircraft's wings, with a subsequent loss of control of the
aircraft. The first Texas Air Aces accident took place
on November 19, 2003, and ANN reported it shortly
thereafter.
AD 2001-13-18 was
issued after an investigation following an
accident involving another T-34, and was
subsequently revised when AD 2001-13-18 R1 was issued. Both
aircraft from Texas Air Aces were compliant with the
AD.
The new Emergency AD does not cancel AD
2001-13-18 R1. The following is the full text of the FAA
notification of Emergency AD 2004-25-51.
EMERGENCY AIRWORTHINESS DIRECTIVE
Aircraft Certification Service
Washington, DC
U.S. Department of Transportation
Federal Aviation Administration
DATE: December 10, 2004
AD #: 2004-25-51
Send to all owners and operators of Raytheon Aircraft Company
(Raytheon) Beech Models 45 (YT-34), A45 (T-34A, B-45), and
D45 (T-34B) airplanes.
Discussion
What events have caused this AD?
On December 7, 2004, the
left wing of a Raytheon Beech Model A45 (T-34A), serial
number G-13, separated from the airplane in flight. The airplane,
operated by Texas Air Aces, crashed near Montgomery, Texas.
The wing was found about a quarter mile away
from the crash site.
The left wing center section failed 4 inches inboard of the
forward wing attach fitting. In addition, FAA investigation
revealed further visual evidence of fatigue (found in other
locations) not previously addressed by AD 2001-13-18 R1,
which FAA issued as a result of an accident near Conroe, Texas.
A review of maintenance records shows that the accident airplane
was in compliance with AD 2001-13-18 R1. AD 2001-13-18 R1 requires
compliance with Raytheon Service Bulletin SB57-3329 to inspect four
locations per wing:
- Location (1) - 9 fasteners at W.S. 34 forward spar;
- Location (2) - the lower rear bathtub fitting;
- Location (3) - 1 fastener at W.S. 64 forward spar; and
- Location (4) - 2 fasteners at W.S. 66 rear spar.
The FAA approved four alternative methods of compliance (AMOCs)
to AD 2001-13-18 R1 based on front spar replacement or modification
and inspections of Location (2) and (4) of the rear spar.
What are the consequences if the condition is not
corrected?
Cracks found in the wings of the affected airplanes could result
in the wing separating from the airplane with consequent loss of
control of the airplane.
What has FAA decided?
After careful review of all available information related to the
subject presented above, FAA has decided to issue an AD to detect
and correct cracking in the wing structure of the affected
airplanes, which could result in the wing separating from the
airplane with consequent loss of control of the airplane.
What does this AD require?
This AD requires you to perform an inspection and/or
modification program approved specifically for this AD by the FAA
Wichita Aircraft Certification Office (ACO).
Presentation of the Actual AD
This rule is issued under 49 U.S.C. Section 44701 (formerly
section 601 of the Federal Aviation Act of 1958), pursuant to the
authority delegated to me by the Administrator, and is effective
immediately upon receipt of this action.
2004-25-51 RAYTHEON AIRCRAFT COMPANY: Directorate
Identifier 2004-CE-44-AD.
When Does This AD Become Effective?
(a) This AD becomes
effective upon receipt of this emergency AD.
Are Any Other ADs Affected By This Action?
(b) None. For clarification, this AD provides no relief from the
requirements of AD 2001-13-18 R1.
What Airplanes Are Affected by This AD?
(c) This AD affects Beech Models 45 (YT-34), A45 (T-34A, B-45),
and D45 (T-34B) airplanes, all serial numbers, that are
certificated in any category.
What is the Unsafe Condition Presented in This
AD?
(d) This AD is the result of cracks found in a location that was
previously inspected and found to comply with AD 2001-13-18 R1; and
two new locations. We are issuing this AD to detect and correct
such cracking, which could result in the wing separating from the
airplane with consequent loss of control of the airplane.
What Must I do to Address This Problem?
(e) The following specifies action you must do per this AD and
other pertinent information to address this problem:
Actions Compliance
(1) Perform an
inspection and/or modification program approved specifically for
this AD by the FAA Wichita Aircraft Certification Office (ACO).
Prior to further flight after the receipt of this emergency
AD.
(2) To return/position the airplane to a home base, hangar,
maintenance facility, etc., you may operate the airplane provided
you follow the limitations in paragraph (f) of this AD. You may
operate the airplane up to 10 hours time-in-service (TIS) provided
the flight(s) occur(s) no later than 30 days after receipt of this
emergency AD.
(3) Special flight permits are allowed for this AD. See
paragraph (f) of this AD for restrictions. Use the procedures
in 14 CFR part 39 and the restrictions in paragraph (f) of this
AD.
(4) To help in the long-term airworthiness solution for the
safety and continued airworthiness of these airplanes, FAA is
requesting data from every owner/operator on the following on these
airplanes:
(i) Service/Repair History (cracked/fatigued structure);
(ii) Maintenance Schedule; and
(iii) Total Hours Time-In-Service (TIS).
Send to:
Paul Nguyen
Aerospace Engineer, FAA
Wichita Aircraft Certification Office
1801 Airport Road
Mid-Continent Airport
Wichita, Kansas 67209
Telephone:(316) 946-4125
Facsimile: (316) 946-4107
e-mail: paul.nguyen@faa.gov
What are the Flight Restrictions Specified in Paragraph
(e)(2) and (e)(3) of this AD?
(f) During the time allowed before compliance with paragraph
(e)(1) of this AD or for any approved special flight permit, you
must adhere to the following limitations:
- NEVER EXCEED SPEED, VNE-175 MPH (152 knots);
- NORMAL ACCELERATION (G) LIMITS – 0, and +2.5;
- ACROBATIC MANEUVERS PROHIBITED.
- FLIGHT INTO KNOWN OR FORECAST MODERATE OR SEVERE TURBULENCE IS
PROHIBITED.
- DAY VISUAL FLIGHT RULES (VFR) OPERATION ONLY.
- PILOT AND ANY ADDITIONAL FLIGHT CREW MEMBER REQUIRED FOR SAFE
OPERATION.
Who do I Contact for Further Information?
(g) If you need additional information relating to this AD,
contact: Paul Nguyen, Aerospace Engineer, FAA, Wichita Aircraft
Certification Office, 1801 Airport Road, Mid-Continent Airport,
Wichita, Kansas 67209; telephone: (316) 946-4125; facsimile: (316)
946-4107; e-mail: paul.nguyen@faa.gov.
Issued in Kansas City, Missouri, on December 10, 2004.
David A. Downey,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.