- Effective
- August 23, 1977
- Superseded by
- AD2000-22-14
- Models
- DC-9-11, DC-9-12, DC-9-13, DC-9-14, DC-9-15, DC-9-15F and 12 more
- Data sheet
- TCDSA6WE
- Registered aircraft
- 13 matched by model
- Product
- Aircraft · Large airplane
- Amendment
- 39-2971
Unofficial copy of the text in the FAA’s Dynamic Regulatory System. The FAA’s own copy is the authoritative one. DRS record last changed August 7, 2025.
Copies of the files this page was built from, with their SHA-256. Retrieved October 18, 2026.
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On this page
The airworthiness directive
77-14-19 MCDONNELL DOUGLAS: Amendment 39-2971. Applies to Model DC-9-10, -20, -30, -40, -50 series and VC-9C (DC-9-32) airplanes certificated in all categories, fuselage numbers, F/N-1 thru F/N-837, which correspond to the factory serial numbers listed in Douglas DC-9 Service Bulletin 54-30 dated January 19, 1977, or later FAA approved revisions.
Compliance required as indicated.
To detect fatigue cracks and/or failure of the engine pylon front spar attachments and upper cap, accomplish the following:
(a) Within the next 1800 flight hours after the effective date of this AD, or before accumulating 9800 total flight hours, whichever occurs later, unless already accomplished within the last 1800 flight hours, and thereafter at intervals not to exceed 3600 flight hours from the last inspection, accomplish radiographic and ultrasonic or eddy current inspections in accordance with the instructions in Douglas Service Bulletin 54-30, dated January 19, 1977, or later FAA approved revision.
For those operators who have conducted only the radiographic inspections per Douglas All Operators Letter, AOL 9-835, dated October 30, 1974, perform the ultrasonic or eddy current inspection, and thereafter, the radiographic and ultrasonic or eddy current inspection per the requirements of this AD, as applicable.
(b) If cracks or failures are found, before further flight, accomplish the modification described in Condition II in Douglas Service Bulletin 54-30 in accordance with the instructions in Douglas Service Bulletin 54-30, dated January 19, 1977, or later FAA approved revision.
(c) The inspections required by paragraph (a) may be discontinued for that pylon(s) upon accomplishment of either or both modifications (Condition I; Condition II) specified in Douglas Service Bulletin 54-30, dated January 19, 1977, or later FAA approved revision.
(d) Equivalent inspection procedures and modifications may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region.
(e) Special flight permits may be issued in accordance with FARs 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections required by this A.D.
This amendment becomes effective August 23, 1977.
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.
Registered aircraft · 13
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.
| 1966 | 1 |
|---|---|
| 1967 | 4 |
| 1969 | 2 |
| 1970 | 1 |
5 with no year recorded