AD 97-03-05
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | The Boeing Company | DC-9-11 | Airworthiness Directives; McDonnell Douglas Model DC-9 Series Airplanes |
| aircraft | The Boeing Company | DC-9-12 | Airworthiness Directives; McDonnell Douglas Model DC-9 Series Airplanes |
| aircraft | The Boeing Company | DC-9-13 | Airworthiness Directives; McDonnell Douglas Model DC-9 Series Airplanes |
| aircraft | The Boeing Company | DC-9-14 | Airworthiness Directives; McDonnell Douglas Model DC-9 Series Airplanes |
| aircraft | The Boeing Company | DC-9-15 | Airworthiness Directives; McDonnell Douglas Model DC-9 Series Airplanes |
| aircraft | The Boeing Company | DC-9-15F | Airworthiness Directives; McDonnell Douglas Model DC-9 Series Airplanes |
| aircraft | The Boeing Company | DC-9-21 | Airworthiness Directives; McDonnell Douglas Model DC-9 Series Airplanes |
| aircraft | The Boeing Company | DC-9-31 | Airworthiness Directives; McDonnell Douglas Model DC-9 Series Airplanes |
| aircraft | The Boeing Company | DC-9-32 | Airworthiness Directives; McDonnell Douglas Model DC-9 Series Airplanes |
| aircraft | The Boeing Company | DC-9-32 (VC-9C) | Airworthiness Directives; McDonnell Douglas Model DC-9 Series Airplanes |
Unsafe Condition
Rapid decompression of the fuselage, significant structural damage, and subsequent reduced structural integrity due to corrosion and fatigue cracking in the fuselage forward upper skin and frames in the area of the ADF loop antenna assemblies.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Perform an internal visual inspection to detect corrosion and cracking of the fuselage forward upper skin and frames in the ADF antenna area per Alert Service Bulletin DC9-53A282. If corrosion or cracking within SRM limits is found, repair per SRM Chapter 53-04, Figure 29. If outside limits, repair with FAA-approved method. Also perform a visual and eddy current inspection of the fuselage forward upper skin under the antennas, followed by antenna reinstallation using an improved procedure as terminating action.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 15 days after April 15, 1996 (effective date of AD 96-07-51), and thereafter at intervals not to exceed 6 months unless repaired. The terminating action must be accomplished within the compliance time extended to 48 months from the AD effective date for airplanes previously repaired under AD 96-07-51.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
McDonnell Douglas Model DC-9 series airplanes with fuselage numbers 001 through 631 inclusive, certificated in any category.
AI-generated summary from the source AD text. Verify against the official source before acting.
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
This site is not affiliated with or endorsed by the FAA. Always verify with official sources.