Airworthiness Directive

AD 2003-19-14 R2 70 FR 59258 Active

Federal Aviation Administration · 14 CFR part 39

Requires you to modify the airspeed indicators, install flight speed reduction and aerobatic maneuver restrictions placards (as applicable), and revise the flight and maintenance manuals.

FR document
05-19929
Amendment
39-14322
Published
2005-10-12
Effective
2005-11-30
Models covered
1

Last live check: 2026-08-19

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AD

2003-19-14 R2

FR doc 05-19929 · 70 FR 59258

AD 2003-19-14 R2Published 2005-10-12Effective 2005-11-30

Revises 2003-19-14 R1

Supersedence is read from the Federal Register text of the newer AD — the FAA publishes no structured field for it — and names only ADs held in our index.

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 modify the airspeed indicators, install flight speed reduction and aerobatic maneuver restrictions placards (as applicable), and revise the flight and maintenance manuals.

Full official abstract

The FAA is revising Airworthiness Directive (AD) 2003-19-14 R1, which applies to certain BURKHART GROB LUFT--UND RAUMFAHRT GmbH & CO KG (GROB) Models G103 TWIN ASTIR, G103A TWIN II ACRO, and G103C TWIN III ACRO sailplanes. AD 2003-19-14 R1 requires you to modify the airspeed indicators, install flight speed reduction and aerobatic maneuver restrictions placards (as applicable), and revise the flight and maintenance manuals. AD 2003-19-14 R1 approves simple aerobatic maneuvers for Model G103A TWIN II ACRO sailplanes and provides an option for modifying the rear fuselage for Models G103A TWIN II ACRO and G103C TWIN III ACRO sailplanes to terminate the flight limitation restrictions for aerobatic maneuvers. This AD retains all the actions from AD 2003-19-14 R1 for Models G103A TWIN II ACRO and G103C TWIN III ACRO and reinstates certain operating limits for Model G103 TWIN ASTIR sailplanes. We are issuing this AD to prevent damage to the fuselage during limit load flight, which could result in reduced structural integrity. This condition could lead to loss of control of the sailplane.

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Applies to 1 model in our index