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Airworthiness Directive

AD 2003-05-05 68 FR 12799 Active

Federal Aviation Administration · 14 CFR part 39

Requires you to inspect the fuselage to determine if a steel fuselage center-section tie bar fitted with bushings in the end lug bolt holes is installed.

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FR document
03-6045
Amendment
39-13081
Published
2003-03-18
Effective
2003-04-25
Models covered
1

Last live check: 2026-08-19

Printed from https://aircraftdirectives.com/ad/2003-05-05 · AircraftDirectives restates official FAA and manufacturer records; the official sources named on this sheet control. Not an airworthiness determination.

This page is a reference Record, not an airworthiness or compliance determination. Official FAA and manufacturer sources control over our restatement, subject to governing law. Check applicability, current requirements and incorporated documents before acting. The owner or operator remains responsible for airworthiness and required records under 14 CFR 91.403 and 91.417, as applicable. Terms of Use: /terms.

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AD

2003-05-05

FR doc 03-6045 · 68 FR 12799

AD 2003-05-05Published 2003-03-18Effective 2003-04-25

FAA rule - 14 CFR 39

FAA rule. Compliance with an applicable AD is required under 14 CFR 39.7. Check its effective date, applicability, compliance times and current status.

Requires you to inspect the fuselage to determine if a steel fuselage center-section tie bar fitted with bushings in the end lug bolt holes is installed.

Full official abstract

This amendment adopts a new airworthiness directive (AD) that applies to certain Robert E. Rust (R.E. Rust) Models DeHavilland DH.C1 Chipmunk 21, 22, and 22A airplanes. This AD requires you to inspect the fuselage to determine if a steel fuselage center-section tie bar fitted with bushings in the end lug bolt holes is installed. If this bushed steel fuselage center-section tie bar is installed, this AD decreases the safe life limit. This AD is the result of reports that certain replacement steel fuselage center-section tie bars installed on the affected airplanes could fail before the originally published safe life limit. The actions specified by this AD are intended to prevent early failure of these bushed steel fuselage center-section tie bars, which could result in reduced structural integrity of the wings. Such a condition could lead to loss of control of the airplane.

More directives for de Havilland DHC-1 Chipmunk

  1. AD 2010-18-12 Airworthiness Directives; Robert E. Rust, Jr. Model DeHavilland DH.C1 Ch... Effective 2010-10-07
  2. AD 2003-17-16 Airworthiness Directives; Robert E. Rust Models DeHavilland DH.C1 Chipmu... Effective 2003-10-10
  3. AD 2003-05-06 Airworthiness Directives; Robert E. Rust Models DeHavilland DH.C1 Chipmu... Effective 2003-04-25

All de Havilland DHC-1 Chipmunk directives

View on Federal Register (opens in a new tab) View this AD in FAA DRS (opens in a new tab) Print AD packet (opens the full Federal Register document in a new tab)

Applies to 1 model in our index